US20100293967A1 - Compressor system and method for gas liquefaction system - Google Patents
Compressor system and method for gas liquefaction system Download PDFInfo
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- US20100293967A1 US20100293967A1 US12/746,131 US74613108A US2010293967A1 US 20100293967 A1 US20100293967 A1 US 20100293967A1 US 74613108 A US74613108 A US 74613108A US 2010293967 A1 US2010293967 A1 US 2010293967A1
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Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25J—LIQUEFACTION, SOLIDIFICATION OR SEPARATION OF GASES OR GASEOUS OR LIQUEFIED GASEOUS MIXTURES BY PRESSURE AND COLD TREATMENT OR BY BRINGING THEM INTO THE SUPERCRITICAL STATE
- F25J1/00—Processes or apparatus for liquefying or solidifying gases or gaseous mixtures
- F25J1/0002—Processes or apparatus for liquefying or solidifying gases or gaseous mixtures characterised by the fluid to be liquefied
- F25J1/0022—Hydrocarbons, e.g. natural gas
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/005—Adaptations for refrigeration plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/08—Adaptations for driving, or combinations with, pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
- F01K13/00—General layout or general methods of operation of complete plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/10—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor
- F02C3/103—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor the compressor being of the centrifugal type
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25J—LIQUEFACTION, SOLIDIFICATION OR SEPARATION OF GASES OR GASEOUS OR LIQUEFIED GASEOUS MIXTURES BY PRESSURE AND COLD TREATMENT OR BY BRINGING THEM INTO THE SUPERCRITICAL STATE
- F25J1/00—Processes or apparatus for liquefying or solidifying gases or gaseous mixtures
- F25J1/003—Processes or apparatus for liquefying or solidifying gases or gaseous mixtures characterised by the kind of cold generation within the liquefaction unit for compensating heat leaks and liquid production
- F25J1/0047—Processes or apparatus for liquefying or solidifying gases or gaseous mixtures characterised by the kind of cold generation within the liquefaction unit for compensating heat leaks and liquid production using an "external" refrigerant stream in a closed vapor compression cycle
- F25J1/0052—Processes or apparatus for liquefying or solidifying gases or gaseous mixtures characterised by the kind of cold generation within the liquefaction unit for compensating heat leaks and liquid production using an "external" refrigerant stream in a closed vapor compression cycle by vaporising a liquid refrigerant stream
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25J—LIQUEFACTION, SOLIDIFICATION OR SEPARATION OF GASES OR GASEOUS OR LIQUEFIED GASEOUS MIXTURES BY PRESSURE AND COLD TREATMENT OR BY BRINGING THEM INTO THE SUPERCRITICAL STATE
- F25J1/00—Processes or apparatus for liquefying or solidifying gases or gaseous mixtures
- F25J1/02—Processes or apparatus for liquefying or solidifying gases or gaseous mixtures requiring the use of refrigeration, e.g. of helium or hydrogen ; Details and kind of the refrigeration system used; Integration with other units or processes; Controlling aspects of the process
- F25J1/0203—Processes or apparatus for liquefying or solidifying gases or gaseous mixtures requiring the use of refrigeration, e.g. of helium or hydrogen ; Details and kind of the refrigeration system used; Integration with other units or processes; Controlling aspects of the process using a single-component refrigerant [SCR] fluid in a closed vapor compression cycle
- F25J1/0208—Processes or apparatus for liquefying or solidifying gases or gaseous mixtures requiring the use of refrigeration, e.g. of helium or hydrogen ; Details and kind of the refrigeration system used; Integration with other units or processes; Controlling aspects of the process using a single-component refrigerant [SCR] fluid in a closed vapor compression cycle in combination with an internal quasi-closed refrigeration loop, e.g. with deep flash recycle loop
- F25J1/0209—Processes or apparatus for liquefying or solidifying gases or gaseous mixtures requiring the use of refrigeration, e.g. of helium or hydrogen ; Details and kind of the refrigeration system used; Integration with other units or processes; Controlling aspects of the process using a single-component refrigerant [SCR] fluid in a closed vapor compression cycle in combination with an internal quasi-closed refrigeration loop, e.g. with deep flash recycle loop as at least a three level refrigeration cascade
- F25J1/021—Processes or apparatus for liquefying or solidifying gases or gaseous mixtures requiring the use of refrigeration, e.g. of helium or hydrogen ; Details and kind of the refrigeration system used; Integration with other units or processes; Controlling aspects of the process using a single-component refrigerant [SCR] fluid in a closed vapor compression cycle in combination with an internal quasi-closed refrigeration loop, e.g. with deep flash recycle loop as at least a three level refrigeration cascade using a deep flash recycle loop
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25J—LIQUEFACTION, SOLIDIFICATION OR SEPARATION OF GASES OR GASEOUS OR LIQUEFIED GASEOUS MIXTURES BY PRESSURE AND COLD TREATMENT OR BY BRINGING THEM INTO THE SUPERCRITICAL STATE
- F25J1/00—Processes or apparatus for liquefying or solidifying gases or gaseous mixtures
- F25J1/02—Processes or apparatus for liquefying or solidifying gases or gaseous mixtures requiring the use of refrigeration, e.g. of helium or hydrogen ; Details and kind of the refrigeration system used; Integration with other units or processes; Controlling aspects of the process
- F25J1/0243—Start-up or control of the process; Details of the apparatus used; Details of the refrigerant compression system used
- F25J1/0244—Operation; Control and regulation; Instrumentation
- F25J1/0245—Different modes, i.e. 'runs', of operation; Process control
- F25J1/0248—Stopping of the process, e.g. defrosting or deriming, maintenance; Back-up mode or systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25J—LIQUEFACTION, SOLIDIFICATION OR SEPARATION OF GASES OR GASEOUS OR LIQUEFIED GASEOUS MIXTURES BY PRESSURE AND COLD TREATMENT OR BY BRINGING THEM INTO THE SUPERCRITICAL STATE
- F25J1/00—Processes or apparatus for liquefying or solidifying gases or gaseous mixtures
- F25J1/02—Processes or apparatus for liquefying or solidifying gases or gaseous mixtures requiring the use of refrigeration, e.g. of helium or hydrogen ; Details and kind of the refrigeration system used; Integration with other units or processes; Controlling aspects of the process
- F25J1/0243—Start-up or control of the process; Details of the apparatus used; Details of the refrigerant compression system used
- F25J1/0279—Compression of refrigerant or internal recycle fluid, e.g. kind of compressor, accumulator, suction drum etc.
- F25J1/0281—Compression of refrigerant or internal recycle fluid, e.g. kind of compressor, accumulator, suction drum etc. characterised by the type of prime driver, e.g. hot gas expander
- F25J1/0283—Gas turbine as the prime mechanical driver
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25J—LIQUEFACTION, SOLIDIFICATION OR SEPARATION OF GASES OR GASEOUS OR LIQUEFIED GASEOUS MIXTURES BY PRESSURE AND COLD TREATMENT OR BY BRINGING THEM INTO THE SUPERCRITICAL STATE
- F25J1/00—Processes or apparatus for liquefying or solidifying gases or gaseous mixtures
- F25J1/02—Processes or apparatus for liquefying or solidifying gases or gaseous mixtures requiring the use of refrigeration, e.g. of helium or hydrogen ; Details and kind of the refrigeration system used; Integration with other units or processes; Controlling aspects of the process
- F25J1/0243—Start-up or control of the process; Details of the apparatus used; Details of the refrigerant compression system used
- F25J1/0279—Compression of refrigerant or internal recycle fluid, e.g. kind of compressor, accumulator, suction drum etc.
- F25J1/029—Mechanically coupling of different refrigerant compressors in a cascade refrigeration system to a common driver
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25J—LIQUEFACTION, SOLIDIFICATION OR SEPARATION OF GASES OR GASEOUS OR LIQUEFIED GASEOUS MIXTURES BY PRESSURE AND COLD TREATMENT OR BY BRINGING THEM INTO THE SUPERCRITICAL STATE
- F25J2230/00—Processes or apparatus involving steps for increasing the pressure of gaseous process streams
- F25J2230/20—Integrated compressor and process expander; Gear box arrangement; Multiple compressors on a common shaft
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25J—LIQUEFACTION, SOLIDIFICATION OR SEPARATION OF GASES OR GASEOUS OR LIQUEFIED GASEOUS MIXTURES BY PRESSURE AND COLD TREATMENT OR BY BRINGING THEM INTO THE SUPERCRITICAL STATE
- F25J2290/00—Other details not covered by groups F25J2200/00 - F25J2280/00
- F25J2290/42—Modularity, pre-fabrication of modules, assembling and erection, horizontal layout, i.e. plot plan, and vertical arrangement of parts of the cryogenic unit, e.g. of the cold box
Definitions
- the present disclosure relates in general to compressor systems, and in particular to compressor systems for use with, for example, gas liquefaction systems, and including aeroderivative gas turbines.
- Embodiments of the disclosure may provide a system including a compressor system through which a refrigerant is adapted to flow, a compressor of the system including a first shaft; and an aeroderivative gas turbine for driving the compressor, the aeroderivative gas turbine including a gas generator; and a low speed power turbine coupled to the gas generator, the low speed power turbine including a second shaft directly coupled to the first shaft of the compressor for directly driving the first shaft; wherein the respective rotational speeds of the first and second shafts are substantially equal.
- Embodiments of the disclosure may further provide a method including providing a compressor including a first shaft; providing an aeroderivative gas turbine including a power turbine including a second shaft; directly coupling the second shaft of the power turbine to the first shaft of the compressor; circulating a refrigerant through the compressor; and pressurizing the refrigerant with the compressor, including directly driving the compressor using the aeroderivative gas turbine, including rotating the first shaft of the power turbine at a first rotational speed; and rotating the second shaft of the compressor at a second rotational speed; wherein the first and second rotational speeds are substantially equal.
- Embodiments of the disclosure may further provide a method including providing a gas liquefaction system including a compressor and an aeroderivative gas turbine coupled thereto, the aeroderivative gas turbine including a gas generator and a power turbine coupled thereto; decoupling the aeroderivative gas turbine from a remainder of the gas liquefaction system as a modular unit; performing maintenance on at least the aeroderivative gas turbine; and re-coupling the aeroderivative gas turbine to the remainder of the gas liquefaction system as a modular unit after decoupling the aeroderivative gas turbine from the remainder of the gas liquefaction system as a modular unit.
- FIG. 1 illustrates a diagram of a system according to an exemplary embodiment, the system including a compressor, an aeroderivative gas turbine, a heat exchanger, a condenser, and an expansion element, such as an expansion valve, according to respective exemplary embodiments.
- FIG. 2 illustrates a partial diagrammatic/partial sectional view of the aeroderivative gas turbine and the compressor of FIG. 1 , according to respective exemplary embodiments.
- FIG. 3 illustrates a partial diagrammatic/partial sectional view of the aeroderivative gas turbine of FIGS. 1 and 2 , according to an exemplary embodiment, the aeroderivative gas turbine including a gas generator and a power turbine, according to respective exemplary embodiments.
- FIG. 4 illustrates a partial diagrammatic/partial sectional view of the power turbine of FIG. 3 , according to an exemplary embodiment.
- FIG. 5 illustrates a partial diagrammatic/partial section view of the compressor of FIGS. 1 and 2 , according to an exemplary embodiment.
- FIG. 6 illustrates a flowchart of a method of operating the system of FIG. 1 , according to an exemplary embodiment.
- FIG. 7 illustrates a flow chart of a step of the method of FIG. 6 , according to an exemplary embodiment.
- FIG. 8 illustrates a flow chart of a step of the step of FIG. 7 , according to an exemplary embodiment.
- FIG. 9 illustrates a flow chart of a step of the step of FIG. 8 , according to an exemplary embodiment.
- FIG. 10 illustrates a flowchart of a step of the step of FIG. 9 , according to an exemplary embodiment.
- FIG. 11 illustrates a flow chart of a step of the step of FIG. 10 , according to an exemplary embodiment.
- FIG. 12 illustrates a graph of exemplary calculations showing a comparison between the aeroderivative gas turbine of FIGS. 1-4 and another aeroderivative gas turbine, according to respective exemplary embodiments.
- FIG. 13A illustrates a flow chart of a method of performing maintenance on the gas liquefaction system of FIG. 1 , according to an exemplary embodiment.
- FIG. 13B illustrates a flow chart of a step of the method of FIG. 13A , according to an exemplary embodiment.
- FIG. 13C illustrates a flow chart of a method of performing maintenance on the gas liquefaction system of FIG. 1 , according to an exemplary embodiment.
- FIG. 14 illustrates a graph of exemplary calculations showing a comparison between the aeroderivative gas turbine of FIGS. 1-4 and another aeroderivative gas turbine, according to respective exemplary embodiments.
- FIG. 15 illustrates a system according to an exemplary embodiment, the system including the compressor, the aeroderivative gas turbine, the heat exchanger, the condenser, and the expansion valve of FIG. 1 .
- first and second features are formed in direct contact
- additional features may be formed interposing the first and second features, such that the first and second features may not be in direct contact.
- exemplary embodiments presented below may be combined in any combination of ways, i.e., any element from one exemplary embodiment may be used in any other exemplary embodiment, without departing from the scope of the disclosure.
- FIG. 1 illustrates, in an exemplary embodiment, a gas liquefaction system, which is generally referred to by the reference numeral 10 and includes a compressor system 11 including a compressor 12 and an aeroderivative gas turbine 14 coupled thereto, the aeroderivative gas turbine 14 including a gas generator 16 and a power turbine 18 coupled thereto.
- the compressor 12 is directly coupled to the aeroderivative gas turbine 14 via a coupling 20 .
- a center axis 22 is defined by the compressor 12 , the aeroderivative gas turbine 14 , and the direct coupling therebetween.
- the compressor 12 is fluidicly coupled between a heat exchanger 24 and a condenser 26 via lines 28 and 30 , respectively.
- An expansion element such as an expansion valve 32
- An expansion element is fluidicly coupled between the condenser 26 and the heat exchanger 24 via lines 34 and 36 , respectively.
- the heat exchanger 24 , the compressor 12 , the condenser 26 , the expansion valve 32 , and the lines 28 , 30 , 34 and 36 together form, or are at least a part of, a loop 38 , through which a refrigerant is adapted to circulate in a direction indicated by arrows 40 , 42 , 44 and 46 , under conditions to be described below.
- the heat exchanger 24 is also fluidicly coupled between lines 48 and 50 , via which a gas is adapted to enter and exit, respectively, the heat exchanger 24 , as indicated by arrows 52 and 54 .
- one or more of the loop 38 and the lines 48 and 50 are, include, or are at least a part of, one or more cooling stages of the gas liquefaction system 10 , under conditions to be described below.
- another expansion element is fluidicly coupled between the condenser 26 and the heat exchanger 24 via the lines 34 and 36 , respectively, such as, for example, a turbo expander, another type of expansion equipment, and/or any combination thereof.
- the power turbine 18 includes a rotatable drive shaft 56 having opposing end portions 56 a and 56 b
- the compressor 12 includes a rotatable compressor shaft 58 having opposing end portions 58 a and 58 b
- the coupling 20 includes opposing end portions 20 a and 20 b .
- Each of the shafts 56 and 58 is generally axially aligned with the center axis 22 .
- the end portion 20 a of the coupling 20 is coupled to the end portion 56 b of the shaft 56 of the power turbine 18
- the end portion 20 b of the coupling 20 is coupled to the end portion of the 58 a of the shaft 58 of the compressor 12 .
- the coupling 20 includes one or more couplings such as, for example, one or more spools.
- the coupling 20 includes one or more couplings such as, for example, one or more spools, which are configured to directly couple the shaft 56 to the shaft 58 so that the shaft 56 directly drives the shaft 58 , under conditions to be described below.
- the coupling 20 is omitted and the end portion 56 b of the shaft 56 is coupled to the end portion 58 a of the shaft 58 so that the shaft 56 directly drives the shaft 58 , under conditions to be described below.
- the coupling 20 in addition to, or instead of one or more couplings such as, for example, one or more spools, the coupling 20 includes one or more other types of devices and/or systems configured to directly couple the shaft 56 to the shaft 58 so that the shaft 56 directly drives the shaft 58 .
- the gas generator 16 of the aeroderivative gas turbine 14 includes an inlet 60 and an outlet 62 fluidicly coupled thereto, and a housing 64 .
- a compressor 66 is disposed in the housing 64 and is fluidicly coupled to the inlet 62 .
- the compressor 66 includes one or more axial compressors.
- a combustion chamber 68 including a combustor 70 is fluidicly coupled between the compressor 66 and the outlet 62 .
- the inlet 60 is fluidicly coupled to one or more lines, chutes, pipes, conduits or the like (not shown) via which air is adapted to be directed to the inlet 60 , under conditions to be described below.
- the power turbine 18 of the aeroderivative gas turbine 14 includes a casing 72 , an intake 74 fluidicly coupled to the outlet 62 of the gas generator 16 , and an exhaust 76 fluidicly coupled to the intake 74 .
- a turbine chamber 78 is fluidicly coupled between the intake 74 and the exhaust 76 .
- a plurality of expansion stages 80 are disposed within the turbine chamber 78 .
- the power turbine 18 weighs about 3,255 lbs.
- the exhaust 76 is fluidicly coupled to one or more lines, chutes, pipes, conduits or the like (not shown) via which hot gas is adapted to be directed away from the exhaust 76 , under conditions to be described below.
- the plurality of expansion stages 80 of the power turbine 18 of the aeroderivative gas turbine 14 includes six (6) expansion stages, namely expansion stages 80 a , 80 b , 80 c , 80 d , 80 e and 80 f , each of which includes a rotor blade 82 and a static nozzle vane 84 disposed proximate thereto.
- Each of the static nozzle vanes 84 is coupled to the casing 72 of the power turbine 18 .
- each of the static nozzle vanes 84 is coupled to the casing 72 of the power turbine 18 by a separate annular shroud (not shown).
- Each of the rotor blades 82 is coupled to, and extends radially outwardly away from, the shaft 56 , and is adapted to rotate within the casing 72 , under conditions to be described below.
- a rotor 86 is coupled to the shaft 56
- each of the rotor blades 82 is coupled to, and extends radially outwardly away from, the rotor 86 , thereby providing the coupling between blades 82 and the shaft 56 .
- the power turbine 18 is a low speed power turbine (LSPT) and the expansion stages 80 a , 80 b , 80 c , 80 d , 80 e and 80 f of the power turbine 18 are configured to drive the shaft 56 and thus the shaft 58 at a rotational speed of about 3,600 rotations per minute (rpm), under conditions to be described below.
- LSPT low speed power turbine
- the power turbine 18 is a low speed power turbine (LSPT) and the expansion stages 80 a , 80 b , 80 c , 80 d , 80 e and 80 f of the power turbine 18 are configured to drive the shaft 56 and thus the shaft 58 at a rotational speed of about 3,600 rotations per minute (rpm), and to produce a power rating of less than about 55,000 horsepower (hp), under conditions to be described below.
- LSPT low speed power turbine
- the power turbine 18 is a low speed power turbine (LSPT) and the expansion stages 80 a , 80 b , 80 c , 80 d , 80 e and 80 f of the power turbine 18 are configured to drive the shaft 56 and thus the shaft 58 at a rotational speed of less than about 3,800 rotations per minute (rpm), and to produce a power rating of less than about 50,000 horsepower (hp), under conditions to be described below.
- the plurality of expansion stages 80 of the power turbine 18 instead of six (6) expansion stages, includes four (4) expansion stages.
- the plurality of expansion stages 80 of the power turbine 18 includes a different quantity of expansion stages.
- the power turbine 18 is configured to drive the shaft 56 and thus the shaft 58 at a rotational speed within a predetermined range of rotational speeds, under conditions to be described below. In an exemplary embodiment, the power turbine 18 is configured to drive the shaft 56 and thus the shaft 58 at a rotational speed ranging from about 2,000 rpm to about 4,000 rpm, under conditions to be described below. In an exemplary embodiment, the maximum speed at which the power turbine 18 is configured to drive the shaft 56 and thus the shaft 58 is about 3,780 rpm. In an exemplary embodiment, the power turbine 18 has an ISO rating (15 degrees C.) of 45,100 horsepower, with a peak power of about 49,900 horsepower near ⁇ 5 degrees C.
- the power turbine 18 has a power rating of less than about 55,000 horsepower (hp). In an exemplary embodiment, the power turbine 18 has a power rating of less than about 50,000 horsepower (hp). In an exemplary embodiment, the power turbine 18 is a modular unit of the aeroderivative gas turbine 14 , and is permitted to be decoupled from, and re-coupled to, the gas generator 16 as a modular unit, under conditions to be described below. In an exemplary embodiment, the power turbine 18 weighs about 3,255 lbs.
- the aeroderivative gas turbine 14 has a relatively low weight.
- the gas generator 16 has a weight ranging from about 4,590 lbs to about 7,625 lbs.
- the aeroderivative gas turbine 14 has a weight ranging from about 7,845 lbs to about 10,880 lbs.
- the aeroderivative gas turbine 14 is an LM2500+G4 LSPT aeroderivative gas turbine having a low speed power turbine (LSPT) with six (6) expansion stages, which type of aeroderivative gas turbine is commercially available from GE Aviation, Evendale, Ohio, USA, which is a subsidiary of the General Electric Company, Fairfield, Conn., USA.
- the aeroderivative gas turbine 14 is another type of commercially available aeroderivative gas turbine.
- the compressor 12 includes a casing 88 , an inlet 90 , and an outlet (not shown) fluidicly coupled to the inlet 90 .
- a plurality of impellers 92 are coupled to the shaft 58 and are configured to rotate along with shaft 58 , under conditions to be described below.
- the compressor 12 is configured to operate with a refrigerant flowing therethrough at a flow rate ranging from about 40,000 actual cubic feet per minute (ACFM) to about 70,000 ACFM, with the shaft 58 being directly driven by the shaft 56 of the power turbine 18 of the aeroderivative gas turbine 14 at a rotational speed ranging from about 2,000 rpm to about 4,000 rpm, thereby pressurizing the refrigerant to a pressure upon discharge from the compressor 12 ranging from about 30 pounds per square inch absolute (psia) to about 300 psia, under conditions to be described below.
- ACFM actual cubic feet per minute
- psia pounds per square inch absolute
- the compressor 12 is configured to operate with a refrigerant flowing therethrough at a flow rate ranging from about 40,000 actual cubic feet per minute (ACFM) to about 70,000 ACFM, with the shaft 58 being directly driven by the shaft 56 of the power turbine 18 of the aeroderivative gas turbine 14 at a rotational speed of about 3,600 rpm, thereby pressurizing the refrigerant to a pressure upon discharge from the compressor 12 ranging from about 30 psia to about 300 psia, under conditions to be described below.
- the compressor 12 is, includes, or is at least a part of, a centrifugal compressor.
- the compressor 12 is a DATUM® centrifugal compressor, which type of compressor is commercially available from the Dresser-Rand Company, Houston, Tex., USA. In an exemplary embodiment, the compressor 12 is another type of commercially available centrifugal compressor.
- a method of operating the system 10 is generally referred to by the reference numeral 96 and includes receiving a fluid in a gas state into the system 10 in step 98 , converting at least a portion of the fluid from the gas state into a liquid state in step 100 including subjecting the fluid to one or more cooling stages in step 102 , and discharging the fluid from the system 10 in step 104 .
- the fluid in the gas state received into the system 10 in the step 98 is natural gas, and at least a portion of the fluid is liquefied natural gas when the fluid is discharged from the system 10 in the step 104 .
- subjecting the fluid to one or more cooling stages in the step 102 includes receiving the fluid into the heat exchanger 24 via the line 48 in step 106 , removing heat from the fluid using the heat exchanger 24 in step 108 , and discharging the fluid from the heat exchanger 24 via the line 50 in step 110 .
- a refrigerant is circulated through the loop 38 in step 112 , and heat is transferred from the fluid to the refrigerant in step 114 during the circulation of the refrigerant through the loop 38 in the step 112 .
- the refrigerant continually flows through the compressor 12 , the line 30 , the condenser 26 , the line 34 , the expansion valve 32 , the line 36 , the heat exchanger 24 , and the line 28 , as indicated by the arrows 40 , 42 , 44 and 46 (shown in FIG. 1 ).
- the refrigerant circulated through the loop 38 in the step 112 is propane. In an exemplary embodiment, the refrigerant circulated through the loop 38 in the step 112 is ethylene. In an exemplary embodiment, the refrigerant circulated through the loop 38 in the step 112 is methane. In an exemplary embodiment, the refrigerant circulated through the loop 38 in the step 112 is a gas with relatively high molecular weight.
- the refrigerant is compressed using the compressor 12 in step 116 , thereby pressurizing the refrigerant. Heat is removed from the refrigerant using the condenser 26 in step 118 , and the refrigerant is expanded using the expansion valve 106 in step 120 . Heat is transferred from the fluid flowing through the heat exchanger 24 and into the refrigerant flowing through the heat exchanger 24 in step 122 .
- the steps 116 , 118 , 120 and 122 are continually repeated during the circulation of the refrigerant through the loop 38 in the step 114 .
- the steps 116 , 118 , 120 and 122 together form, or are at least a part of, one or more refrigeration cycles.
- the refrigerant is received into the compressor 12 via the line 28 and the inlet 90 in step 124 , the shaft 58 is directly driven by the aeroderivative gas turbine 14 to thereby rotate the impellers 92 and pressurize the refrigerant in step 126 , and the pressurized refrigerant is discharged from the compressor 12 and into the line 30 in step 128 .
- the flow rate of the refrigerant ranges from about 40,000 ACFM to about 70,000 ACFM.
- the pressurized refrigerant is discharged from the compressor 12 in the step 128 at a pressure ranging from about 30 psia to about 300 psia.
- the shaft 58 of the compressor 12 is directly driven by the aeroderivative gas turbine 14 so that the shaft 58 rotates in place about the axis 22 at a rotational speed ranging from about 2,000 rpm to about 4,000 rpm.
- the shaft 58 of the compressor 12 is directly driven by the aeroderivative gas turbine 14 so that the shaft 58 rotates in place about the axis 22 at a rotational speed of about 3,600 rpm.
- the hot gas is directed through the expansion stages 80 a , 80 b , 80 c , 80 d , 80 e and 80 f of the power turbine 18 in step 138 , thereby causing the shaft 56 of the power turbine 18 to rotate in place about the axis 22 , which, in turn, directly drives the shaft 58 of the compressor 12 . More particularly, as the hot gas flows through each of the stages 80 a , 80 b , 80 c , 80 d , 80 e and 80 f , the corresponding static nozzle vane 84 directs the hot gas against the corresponding rotor blade 82 , thereby causing torque to be exerted on the shaft 56 , thereby causing the shaft 56 to rotate in place about the axis 22 .
- the rotation of the shaft 56 in the step 138 directly drives the shaft 58 , causing the shaft 58 of the compressor 12 to rotate during the rotation of the shaft 56 of the power turbine 18 in step 140 .
- the respective rotational speeds of the shafts 56 and 58 are substantially equal.
- the rotational speed of each of the shafts 56 and 58 ranges from about 2,000 rpm to about 4,000 rpm.
- the rotational speed of each of the shafts 56 and 58 is about 3,600 rpm.
- the hot gas exits the power turbine 18 and thus the aeroderivative gas turbine 14 via the exhaust 76 of the power turbine 18 in step 142 .
- the steps 132 , 134 , 136 , 138 , 140 and 142 occur simultaneously and/or are continually repeated.
- the above-described direct coupling of the shaft 56 of the power turbine 18 of the aeroderivative gas turbine 14 to the shaft 58 of the compressor 12 permits the shaft 56 to directly drive the shaft 58 in the step 126 . Since the shaft 56 directly drives the shaft 58 of the compressor 12 in the step 126 , no speed-changing devices, such as, for example, gearboxes, gearing and/or similar mechanisms, are necessary for the shaft 56 to drive the shaft 58 .
- the above-described direct coupling between the shafts 56 and 58 eliminates the need for a gearbox.
- the elimination of the need for a speed-changing device, such as a gearbox, to drive the compressor 12 provides additional liquefaction of the gas flowing into the heat exchanger 24 via the line 48 due to increased compressor throughput that arises from the recovery of friction power losses that are associated with a gearbox, which are typically on the order of about 1.5%. Further, the elimination of the need for a gearbox to drive the compressor 12 provides incremental equipment reliability and availability due to the elimination of a major piece of rotating machinery. Still further, the elimination of the need for a gearbox to drive the compressor 12 provides a reduced installation footprint by eliminating the gearbox from the line of rotating machinery.
- exemplary calculations were conducted, the calculation results of which indicated that the use of the aeroderivative gas turbine 14 having the low speed power turbine (LSPT) 18 with the six (6) expansion stages 80 a , 80 b , 80 c , 80 d , 80 e and 80 f , which could be, for example, an LM2500+G4 LSPT aeroderivative gas turbine having a low speed power turbine (LSPT) with six (6) expansion stages, which type of aeroderivative gas turbine is commercially available from GE Aviation, Evendale, Ohio, USA, would provide more shaft power than the use of an aeroderivative gas turbine having a high speed power turbine (HSPT) with two (2) expansion stages, which could be, for example, an LM2500+G4 HSPT aeroderivative gas turbine having a high speed power turbine (HSPT) with two (2) expansion stages, which type of high speed power turbine may be a Dresser-
- exemplary calculation results were unexpected. More particularly, as shown in FIG. 12 , exemplary calculations were conducted using the gas turbine manufacturer's performance cycle program in accordance with ASME PTC 22-2005, the calculation results of which indicated that, with the performance basis and all other parameters being the same, the use of the aeroderivative gas turbine 14 having the low speed power turbine (LSPT) 18 with the six (6) expansion stages 80 a , 80 b , 80 c , 80 d , 80 e and 80 f , which could be, for example, an LM2500+G4 LSPT aeroderivative gas turbine having a low speed power turbine (LSPT) with six (6) expansion stages, would offer more shaft power over a range of ambient temperatures, such as, for example, about 1.17% more shaft power at an ambient temperature ranging from about 22 to about 23 degrees C., about 1.57% more shaft power at an ambient temperature of about 27 degrees C., and about 1.38% more shaft power at an ambient temperature ranging from about 32 to about 33 degrees C., as compared to
- a method of performing maintenance on the gas liquefaction system 10 is generally referred to by the reference numeral 144 and includes decoupling the aeroderivative gas turbine 14 , including the gas generator 16 and the power turbine 18 , as a modular unit from the remainder of the system 10 in step 146 .
- the aeroderivative gas turbine 14 is re-coupled to the remainder of the system 10 as a modular unit in step 150 .
- the aeroderivative gas turbine 14 is decoupled as a modular unit. More particularly, the inlet 60 of the gas generator 16 of the aeroderivative gas turbine 14 is decoupled in step 152 from one or more lines, chutes, pipes, conduits or the like (not shown) via which air is directed to the gas generator 16 .
- the exhaust 76 is decoupled in step 154 from one or more lines, chutes, pipes, conduits or the like (not shown) via which hot gas is directed away from the power turbine 18 .
- the shaft 56 of the power turbine 18 is decoupled from the shaft 58 of the compressor 12 in step 156 , which, in an exemplary embodiment, includes decoupling the end portion 56 b of the shaft 56 of the power turbine 18 of the aeroderivative gas turbine 14 from the end portion 20 a of the coupling 20 .
- the step 156 includes one or more of the following: decoupling the coupling 20 from the shaft 58 of the compressor 12 ; decoupling the shaft 56 of the power turbine 18 from the coupling 20 ; decoupling the shaft 56 of the power turbine 18 from the shaft 58 of the compressor 12 ; decoupling the end portion 20 b from the end portion 58 a ; and decoupling the end portion 56 b from the end portion 58 a .
- the power turbine 18 is decoupled from the gas generator 16 as a modular unit.
- the inlet 60 of the gas generator 16 of the aeroderivative gas turbine 14 is re-coupled to one or more lines, chutes, pipes, conduits or the like (not shown) via which air is directed to the gas generator 16
- the exhaust 76 is re-coupled to one or more lines, chutes, pipes, conduits or the like (not shown) via which hot gas is directed away from the power turbine 18
- the shaft 56 of the power turbine 18 is re-coupled to the shaft 58 of the compressor 12 , which, in an exemplary embodiment, includes re-coupling the end portion 56 b of the shaft 56 of the power turbine 18 of the aeroderivative gas turbine 14 to the end portion 20 a of the coupling 20 .
- re-coupling the shaft 56 to the shaft 58 includes one or more of the following: re-coupling the coupling 20 to the shaft 58 of the compressor 12 ; re-coupling the shaft 56 of the power turbine 18 to the coupling 20 ; re-coupling the shaft 56 of the power turbine 18 to the shaft 58 of the compressor 12 ; re-coupling the end portion 20 b to the end portion 58 a ; and re-coupling the end portion 56 b to the end portion 58 a .
- the power turbine 18 before, during and/or after the steps 146 , 148 and/or 150 , the power turbine 18 is re-coupled to the gas generator 16 as a modular unit.
- a method of performing maintenance on the gas liquefaction system 10 is generally referred to by the reference numeral 157 and includes decoupling the aeroderivative gas turbine 14 , including the gas generator 16 and the power turbine 18 , as a modular unit from the remainder of the system 10 in step 157 a .
- a spare aeroderivative gas turbine which is substantially similar to the aeroderivative gas turbine 14 , is coupled to the remainder of the system 10 as a modular unit in step 157 b , after which the system 10 is operated in step 157 c in accordance with the foregoing.
- step 157 d Before, during and/or after the steps 157 a , 157 b and/or 157 c , maintenance is performed on at least the aeroderivative gas turbine 14 in step 157 d .
- the spare aeroderivative gas turbine Before, during and/or after the step 157 d , the spare aeroderivative gas turbine is decoupled from the remainder of the system 10 in step 157 e .
- the aeroderivative gas turbine 14 Before, during and/or after the steps 157 d and/or 157 e , the aeroderivative gas turbine 14 is re-coupled to the remainder of the system 10 as a modular unit in step 157 f .
- the step 157 a is substantially similar to the step 146 and therefore will not be described in detail.
- the step 157 b is substantially similar to the step 150 and therefore will not be described in detail, except that the spare aeroderivative gas turbine is coupled to the remainder of the system 10 in the step 157 b , rather than the aeroderivative gas turbine 14 .
- the step 157 c is substantially similar to the method 96 and therefore will not be described in detail, except that the system 10 is operated with the spare aeroderivative gas turbine in the step 157 c , rather than the aeroderivative gas turbine 14 .
- the step 157 d is substantially similar to the step 148 and therefore will not be described in detail.
- the step 157 e is substantially similar to either the step 146 or the step 157 a and therefore will not be described in detail, except that the spare aeroderivative gas turbine is decoupled from the remainder of the system 10 in the step 157 e , rather the aeroderivative gas turbine 14 .
- the step 157 f is substantially similar to the step 150 and therefore will not be described in detail.
- the modularity of the aeroderivative gas turbine 14 results in a substantial reduction in “down time” in that, during routine maintenance, the aeroderivative gas turbine 14 and/or its components such as the gas generator 16 and/or the power turbine 18 do not need to be disassembled in place in the system 10 and/or while the aeroderivative gas turbine 14 is coupled to the compressor 12 .
- the modularity of the aeroderivative gas turbine 14 i.e., the ability to decouple the aeroderivative gas turbine 14 from the remainder of the system 10 as a modular unit in the step 146 or 157 a , translates to up to ten (10) or more days of production over a typical project evaluation life cycle, thereby providing substantially greater economic return on the capital investment of the owner(s) of the system 10 .
- exemplary calculations were conducted, the calculation results of which indicated that the use of the aeroderivative gas turbine 14 having the low speed power turbine (LSPT) 18 with the six (6) expansion stages 80 a , 80 b , 80 c , 80 d , 80 e and 80 f , which could be, for example, an LM2500+G4 LSPT aeroderivative gas turbine having a low speed power turbine (LSPT) with six (6) expansion stages, which type of aeroderivative gas turbine is commercially available from GE Aviation, Evendale, Ohio, USA, would reduce the cost associated with cumulative loss of production as a result of “down time” for routine and/or scheduled maintenance of at least the aeroderivative gas turbine 14 , that is, the cost associated with not being able to convert as much of the fluid as possible into a liquid state in the step 100 of the method 96 because the aeroderivative gas turbine 14 and the compressor 12 are in
- exemplary calculations were conducted, the calculation results of which indicated that, with the performance basis and all other parameters being the same, the use of the aeroderivative gas turbine 14 having the low speed power turbine (LSPT) 18 with the six (6) expansion stages 80 a , 80 b , 80 c , 80 d , 80 e and 80 f , which could be, for example, an LM2500+G4 LSPT aeroderivative gas turbine having a low speed power turbine (LSPT) with six (6) expansion stages, in accordance with the method 157 , would provide a cost savings associated with cumulative loss of production as a result of “down time” for routine and/or scheduled maintenance over the operational life of the aeroderivative gas turbine 14 of, for example, about $10,000,000 after an operational time period of about eight years, and about $27,000,000 after an operational time period of about twenty five years, as compared to the use of an aeroderivative gas turbine having a high speed power turbine (HSPT) with two (2) expansion stages, which
- the cost savings shown in FIG. 14 are based on, inter alia, the scheduled maintenance for both the LM2500+G4 LSPT aeroderivative gas turbine and the LM2500+G4 HSPT aeroderivative gas turbine, plant nominal capacity, and incremental sales rather than operating income (OI).
- the shorter maintenance schedule of the aeroderivative gas turbine 14 having the low speed power turbine (LSPT) 18 with the six (6) expansion stages 80 a , 80 b , 80 c , 80 d , 80 e and 80 f would provide the exemplary calculated cost savings shown in FIG. 14 .
- the execution of the method 157 greatly reduces the amount of days of “down time” of the aeroderivative gas turbine 14 and the compressor 12 .
- the exemplary calculated cost savings shown in FIG. 14 assume that routine and/or scheduled maintenance performed on at least the aeroderivative gas turbine 14 , in accordance with the method 157 , would take no more than about two days.
- a system is generally referred to by the reference numeral 158 and includes several parts of the system 10 , which parts are given the same reference numerals.
- the system 158 further includes a compressor 160 directly coupled to the compressor 12 via a coupling 162 .
- the compressor 160 is fluidicly coupled between the heat exchanger 24 and a condenser 164 via lines 166 and 168 , respectively.
- An expansion element, such as an expansion valve 170 is fluidicly coupled between the condenser 164 and the heat exchanger 24 via lines 172 and 174 , respectively.
- the heat exchanger 24 , the compressor 160 , the condenser 164 , the expansion valve 170 , and the lines 166 , 168 , 172 and 174 together form, or are at least a part of, a loop 176 , through which a refrigerant is adapted to circulate in a direction indicated by arrows 178 , 180 , 182 and 184 .
- the compressor 12 in the system 158 is a double flow compressor
- the compressor 160 is a single flow compressor.
- the operation of the system 158 is similar to the method 96 of operation of the system 10 and will not be described in detail, except that the aeroderivative gas turbine 14 also drives the compressor 160 , in addition to driving the compressor 12 ; the step 112 includes circulating refrigerant through the loop 176 , in addition to circulating refrigerant through the loop 38 ; and the step 114 includes transferring heat from the fluid, which flows through the line 48 , the heat exchanger 24 , and the line 50 , into the refrigerant circulating through the loop 176 , in addition to the refrigerant circulating through the loop 38 .
- maintenance is performed on the system 158 in a manner substantially similar to the method 144 .
- maintenance is performed on the system 158 in a manner substantially similar to the method 157 .
- one or more other compressors are driven by the aeroderivative gas turbine 14 in the systems 10 and/or 158 .
- one or more waste heat recovery cycles and/or systems are operably coupled to the aeroderivative gas turbine 14 .
- one or more waste heat recovery cycles and/or systems are operably coupled between the aeroderivative gas turbine 14 and the heat exchanger 24 .
- one or more waste heat recovery cycles and/or systems are operably coupled to the aeroderivative gas turbine 14 and one or more other components of the system 10 such as, for example, one or more of the heat exchanger 24 , the line 48 , the line 50 , and/or any combination thereof.
- one or more waste heat recovery cycles and/or systems are operably coupled to the aeroderivative gas turbine 14 and one or more other components of the system 158 such as, for example, one or more of the heat exchanger 24 , the line 48 , the line 50 , and/or any combination thereof.
- a system has been described that includes a compressor system including a compressor through which a refrigerant is adapted to flow, the compressor including a first shaft; and an aeroderivative gas turbine for driving the compressor, the aeroderivative gas turbine including a gas generator; and a low speed power turbine coupled to the gas generator, the low speed power turbine including a second shaft directly coupled to the first shaft of the compressor for directly driving the first shaft; wherein the respective rotational speeds of the first and second shafts are substantially equal.
- the system includes a gas liquefaction system for converting at least a portion of a fluid from a gas state into a liquid state, the fluid in the gas state including natural gas, the fluid in the liquid state including liquefied natural gas, the gas liquefaction system including one or more cooling stages including the refrigerant; and a loop through which the refrigerant is adapted to circulate, the loop including a heat exchanger for transferring heat out of the fluid and into the refrigerant; the compressor of the compressor system for pressurizing the refrigerant; a condenser for transferring heat out of the refrigerant; and an expansion element for expanding the refrigerant; wherein the aeroderivative gas turbine is coupled to the compressor as a modular unit; wherein the low speed power turbine is coupled to the gas generator as a modular unit; wherein the compressor comprises a centrifugal compressor; wherein the refrigerant flows through the centrifugal compressor at a flow rate ranging from about 40,000 actual cubic feet per
- the first and second shafts are generally axially aligned; and wherein the rotational speed of the first and second shafts ranges from about 2,000 revolutions per minute to about 4,000 revolutions per minute.
- the compressor comprises a centrifugal compressor configured so that the refrigerant is adapted to flow through the centrifugal compressor at a flow rate ranging from about 40,000 actual cubic feet per minute to about 70,000 actual cubic feet per minute; and wherein the centrifugal compressor is configured to pressurize the refrigerant so that the pressurized refrigerant is discharged from the centrifugal compressor at a pressure ranging from about 30 pounds per square inch absolute to about 300 pounds per square inch absolute.
- the low speed power turbine includes at least six expansion stages for driving the second shaft; and wherein the at least six expansion stages drives the second shaft so that the low speed power turbine has a power rating of less than about 55,000 horsepower.
- the aeroderivative gas turbine is coupled to the compressor as a modular unit; and wherein the low speed power turbine is coupled to the gas generator as a modular unit.
- the system includes a gas liquefaction system for converting at least a portion of a fluid from a gas state into a liquid state, the fluid in the gas state including natural gas, the fluid in the liquid state including liquefied natural gas, the gas liquefaction system including one or more cooling stages including the refrigerant; and a loop through which the refrigerant is adapted to circulate, the loop including a heat exchanger for transferring heat out of the fluid and into the refrigerant; the compressor of the compressor system for pressurizing the refrigerant; a condenser for transferring heat out of the refrigerant; and an expansion element for expanding the refrigerant.
- a method includes providing a compressor including a first shaft; providing an aeroderivative gas turbine including a power turbine including a second shaft; directly coupling the second shaft of the power turbine to the first shaft of the compressor; circulating a refrigerant through the compressor; and pressurizing the refrigerant with the compressor, including directly driving the compressor using the aeroderivative gas turbine, including rotating the first shaft of the power turbine at a first rotational speed; and rotating the second shaft of the compressor at a second rotational speed; wherein the first and second rotational speeds are substantially equal.
- the method includes converting at least a portion of a fluid from a gas state into a liquid state, the fluid in the gas state including natural gas, the fluid in the liquid state including liquefied natural gas; wherein converting at least a portion of the fluid from the gas state into the liquid state includes transferring heat from the fluid and into the refrigerant; wherein the compressor comprises a centrifugal compressor; wherein the power turbine is a low speed power turbine including at least six expansion stages; wherein circulating the refrigerant through the compressor includes circulating the refrigerant through the compressor at a flow rate ranging from about 40,000 actual cubic feet per minute to about 70,000 actual cubic feet per minute; wherein pressurizing the refrigerant with the compressor includes pressurizing the refrigerant with the compressor so that the pressurized refrigerant is discharged from the compressor at a pressure ranging from about 30 pounds per square inch absolute to about 300 pounds per square inch absolute; wherein rotating the first shaft of the power turbine at the first rotational speed includes driving the first
- the method includes converting at least a portion of a fluid from a gas state into a liquid state, the fluid in the gas state including natural gas, the fluid in the liquid state including liquefied natural gas; wherein converting at least a portion of the fluid from the gas state into the liquid state includes transferring heat from the fluid and into the refrigerant.
- the compressor comprises a centrifugal compressor; wherein circulating the refrigerant through the compressor includes circulating the refrigerant through the compressor at a flow rate ranging from about 40,000 actual cubic feet per minute to about 70,000 actual cubic feet per minute; and wherein pressurizing the refrigerant with the compressor includes pressurizing the refrigerant with the compressor so that the pressurized refrigerant is discharged from the compressor at a pressure ranging from about 30 pounds per square inch absolute to about 300 pounds per square inch absolute.
- the power turbine is a low speed power turbine including at least six expansion stages; and wherein rotating the first shaft of the power turbine at the first rotational speed includes driving the first shaft using the at least six expansion stages so that the low speed power turbine has a power rating of less than about 55,000 horsepower.
- the method includes decoupling the aeroderivative gas turbine from the compressor as a modular unit; performing maintenance on at least the aeroderivative gas turbine; and re-coupling the aeroderivative gas turbine to the compressor as a modular unit.
- decoupling the aeroderivative gas turbine from the compressor as a modular unit includes decoupling the first shaft of the power turbine from the second shaft of the compressor; and wherein re-coupling the aeroderivative gas turbine to the compressor as a modular unit includes re-coupling the first shaft of the power turbine to the second shaft of the compressor.
- the first and second shafts are generally axially aligned; and wherein each of the first and second rotational speeds ranges from about 2,000 revolutions per minute to about 4,000 revolutions per minute.
- a method includes providing a gas liquefaction system including a compressor and an aeroderivative gas turbine coupled thereto, the aeroderivative gas turbine including a gas generator and a power turbine coupled thereto; decoupling the aeroderivative gas turbine from a remainder of the gas liquefaction system as a modular unit; performing maintenance on at least the aeroderivative gas turbine; and re-coupling the aeroderivative gas turbine to the remainder of the gas liquefaction system as a modular unit after decoupling the aeroderivative gas turbine from the remainder of the gas liquefaction system as a modular unit.
- the aeroderivative gas turbine includes an inlet for receiving air into the gas generator; wherein the power turbine includes an exhaust for discharging gas from the power turbine, wherein the exhaust is fluidicly coupled to the inlet when the aeroderivative gas turbine is in the form of the modular unit, and a first shaft; wherein the compressor includes a second shaft directly coupled to the first shaft of the power turbine when the aeroderivative gas turbine is coupled to the compressor; and wherein decoupling the aeroderivative gas turbine from the remainder of the gas liquefaction system as a modular unit includes decoupling the inlet of the gas generator from means via which the air is adapted to be directed to the gas generator; decoupling the exhaust of the power turbine from means via which the gas is adapted to be directed away from the power turbine; and decoupling the first shaft from the second shaft.
- re-coupling the aeroderivative gas turbine to the remainder of the gas liquefaction system as a modular unit includes re-coupling the inlet of the gas generator to the means via which the air is adapted to be directed to the gas generator; re-coupling the exhaust of the power turbine to the means via which the gas is adapted to be directed away from the power turbine; and re-coupling the first shaft to the second shaft.
- the method includes converting at least a portion of a fluid from a gas state into a liquid state, the fluid in the gas state including natural gas, the fluid in the liquid state including liquefied natural gas; wherein converting at least a portion of the fluid from the gas state to the liquid state includes subjecting the fluid to one or more cooling stages, including receiving fluid into a heat exchanger fluidicly coupled to the compressor; removing heat from the fluid using the heat exchanger; and discharging the fluid from the heat exchanger; and wherein removing heat from the fluid using the heat exchanger includes circulating a refrigerant through a loop, the loop including the heat exchanger and the compressor; and transferring heat from the fluid and to the refrigerant during circulating the refrigerant through the loop, including transferring heat from the fluid and to the refrigerant using the heat exchanger; and pressurizing the refrigerant with the compressor, including directly driving the compressor using the aeroderivative gas turbine, including rotating the first shaft of the power turbine at a first rotation
- the method includes coupling a spare aeroderivative gas turbine to the remainder of the gas liquefaction system as a modular unit; operating the gas liquefaction system with the spare aeroderivative gas turbine; and decoupling the spare aeroderivative gas turbine from the remainder of the gas liquefaction system as a modular unit.
- any spatial references such as, for example, “upper,” “lower,” “above,” “below,” “between,” “bottom,” “vertical,” “horizontal,” “angular,” “upwards,” “downwards,” “side-to-side,” “left-to-right,” “left,” “right,” “right-to-left,” “top-to-bottom,” “bottom-to-top,” “top,” “bottom,” “bottom-up,” “top-down,” etc., are for the purpose of illustration only and do not limit the specific orientation or location of the structure described above.
- any means-plus-function clauses are intended to cover the structures described herein as performing the recited function and not only structural equivalents, but also equivalent structures.
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Abstract
A system and method according to which a compressor having a first shaft is provided, and an aeroderivative gas turbine for driving the compressor is provided, the aeroderivative gas turbine including a gas generator and a power turbine coupled to the gas generator, the power turbine having a second shaft directly coupled to the first shaft of the compressor for directly driving the first shaft.
Description
- This application claims the benefit of the filing date of U.S. provisional patent application No. 61/005,701, filed Dec. 7, 2007, the disclosure of which is incorporated herein by reference.
- The present disclosure relates in general to compressor systems, and in particular to compressor systems for use with, for example, gas liquefaction systems, and including aeroderivative gas turbines.
- Embodiments of the disclosure may provide a system including a compressor system through which a refrigerant is adapted to flow, a compressor of the system including a first shaft; and an aeroderivative gas turbine for driving the compressor, the aeroderivative gas turbine including a gas generator; and a low speed power turbine coupled to the gas generator, the low speed power turbine including a second shaft directly coupled to the first shaft of the compressor for directly driving the first shaft; wherein the respective rotational speeds of the first and second shafts are substantially equal.
- Embodiments of the disclosure may further provide a method including providing a compressor including a first shaft; providing an aeroderivative gas turbine including a power turbine including a second shaft; directly coupling the second shaft of the power turbine to the first shaft of the compressor; circulating a refrigerant through the compressor; and pressurizing the refrigerant with the compressor, including directly driving the compressor using the aeroderivative gas turbine, including rotating the first shaft of the power turbine at a first rotational speed; and rotating the second shaft of the compressor at a second rotational speed; wherein the first and second rotational speeds are substantially equal.
- Embodiments of the disclosure may further provide a method including providing a gas liquefaction system including a compressor and an aeroderivative gas turbine coupled thereto, the aeroderivative gas turbine including a gas generator and a power turbine coupled thereto; decoupling the aeroderivative gas turbine from a remainder of the gas liquefaction system as a modular unit; performing maintenance on at least the aeroderivative gas turbine; and re-coupling the aeroderivative gas turbine to the remainder of the gas liquefaction system as a modular unit after decoupling the aeroderivative gas turbine from the remainder of the gas liquefaction system as a modular unit.
- The present disclosure is best understood from the following detailed description when read with the accompanying Figures. It is emphasized that, in accordance with the standard practice in the industry, various features are not drawn to scale. In fact, the dimensions of the various features may be arbitrarily increased or reduced for clarity of discussion.
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FIG. 1 illustrates a diagram of a system according to an exemplary embodiment, the system including a compressor, an aeroderivative gas turbine, a heat exchanger, a condenser, and an expansion element, such as an expansion valve, according to respective exemplary embodiments. -
FIG. 2 illustrates a partial diagrammatic/partial sectional view of the aeroderivative gas turbine and the compressor ofFIG. 1 , according to respective exemplary embodiments. -
FIG. 3 illustrates a partial diagrammatic/partial sectional view of the aeroderivative gas turbine ofFIGS. 1 and 2 , according to an exemplary embodiment, the aeroderivative gas turbine including a gas generator and a power turbine, according to respective exemplary embodiments. -
FIG. 4 illustrates a partial diagrammatic/partial sectional view of the power turbine ofFIG. 3 , according to an exemplary embodiment. -
FIG. 5 illustrates a partial diagrammatic/partial section view of the compressor ofFIGS. 1 and 2 , according to an exemplary embodiment. -
FIG. 6 illustrates a flowchart of a method of operating the system ofFIG. 1 , according to an exemplary embodiment. -
FIG. 7 illustrates a flow chart of a step of the method ofFIG. 6 , according to an exemplary embodiment. -
FIG. 8 illustrates a flow chart of a step of the step ofFIG. 7 , according to an exemplary embodiment. -
FIG. 9 illustrates a flow chart of a step of the step ofFIG. 8 , according to an exemplary embodiment. -
FIG. 10 illustrates a flowchart of a step of the step ofFIG. 9 , according to an exemplary embodiment. -
FIG. 11 illustrates a flow chart of a step of the step ofFIG. 10 , according to an exemplary embodiment. -
FIG. 12 illustrates a graph of exemplary calculations showing a comparison between the aeroderivative gas turbine ofFIGS. 1-4 and another aeroderivative gas turbine, according to respective exemplary embodiments. -
FIG. 13A illustrates a flow chart of a method of performing maintenance on the gas liquefaction system ofFIG. 1 , according to an exemplary embodiment. -
FIG. 13B illustrates a flow chart of a step of the method ofFIG. 13A , according to an exemplary embodiment. -
FIG. 13C illustrates a flow chart of a method of performing maintenance on the gas liquefaction system ofFIG. 1 , according to an exemplary embodiment. -
FIG. 14 illustrates a graph of exemplary calculations showing a comparison between the aeroderivative gas turbine ofFIGS. 1-4 and another aeroderivative gas turbine, according to respective exemplary embodiments. -
FIG. 15 illustrates a system according to an exemplary embodiment, the system including the compressor, the aeroderivative gas turbine, the heat exchanger, the condenser, and the expansion valve ofFIG. 1 . - It is to be understood that the following disclosure describes several exemplary embodiments for implementing different features, structures, or functions of the invention. Exemplary embodiments of components, arrangements, and configurations are described below to simplify the present disclosure, however, these exemplary embodiments are provided merely as examples and are not intended to limit the scope of the invention. Additionally, the present disclosure may repeat reference numerals and/or letters in the various exemplary embodiments and across the Figures provided herein. This repetition is for the purpose of simplicity and clarity and does not in itself dictate a relationship between the various exemplary embodiments and/or configurations discussed in the various Figures. Moreover, the formation of a first feature over or on a second feature in the description that follows may include embodiments in which the first and second features are formed in direct contact, and may also include embodiments in which additional features may be formed interposing the first and second features, such that the first and second features may not be in direct contact. Finally, the exemplary embodiments presented below may be combined in any combination of ways, i.e., any element from one exemplary embodiment may be used in any other exemplary embodiment, without departing from the scope of the disclosure.
- Additionally, certain terms are used throughout the following description and claims to refer to particular components. As one skilled in the art will appreciate, various entities may refer to the same component by different names, and as such, the naming convention for the elements described herein is not intended to limit the scope of the invention, unless otherwise specifically defined herein. Further, the naming convention used herein is not intended to distinguish between components that differ in name but not function. Further, in the following discussion and in the claims, the terms “including” and “comprising” are used in an open-ended fashion, and thus should be interpreted to mean “including, but not limited to.” All numerical values in this disclosure may be exact or approximate values unless otherwise specifically stated. Accordingly, various embodiments of the disclosure may deviate from the numbers, values, and ranges disclosed herein without departing from the intended scope.
-
FIG. 1 illustrates, in an exemplary embodiment, a gas liquefaction system, which is generally referred to by thereference numeral 10 and includes acompressor system 11 including acompressor 12 and anaeroderivative gas turbine 14 coupled thereto, theaeroderivative gas turbine 14 including agas generator 16 and apower turbine 18 coupled thereto. Thecompressor 12 is directly coupled to theaeroderivative gas turbine 14 via acoupling 20. Acenter axis 22 is defined by thecompressor 12, theaeroderivative gas turbine 14, and the direct coupling therebetween. Thecompressor 12 is fluidicly coupled between aheat exchanger 24 and acondenser 26 vialines expansion valve 32, is fluidicly coupled between thecondenser 26 and theheat exchanger 24 vialines heat exchanger 24, thecompressor 12, thecondenser 26, theexpansion valve 32, and thelines loop 38, through which a refrigerant is adapted to circulate in a direction indicated byarrows compressor 12 and theexpansion valve 32 via thelines heat exchanger 24 is also fluidicly coupled betweenlines heat exchanger 24, as indicated byarrows loop 38 and thelines gas liquefaction system 10, under conditions to be described below. In several exemplary embodiments, instead of, or in addition to theexpansion valve 32, another expansion element is fluidicly coupled between thecondenser 26 and theheat exchanger 24 via thelines - In an exemplary embodiment, as illustrated in
FIG. 2 with continuing reference toFIG. 1 , thepower turbine 18 includes arotatable drive shaft 56 havingopposing end portions compressor 12 includes arotatable compressor shaft 58 havingopposing end portions coupling 20 includesopposing end portions shafts center axis 22. Theend portion 20 a of thecoupling 20 is coupled to theend portion 56 b of theshaft 56 of thepower turbine 18, and theend portion 20 b of thecoupling 20 is coupled to the end portion of the 58 a of theshaft 58 of thecompressor 12. In an exemplary embodiment, thecoupling 20 includes one or more couplings such as, for example, one or more spools. In an exemplary embodiment, thecoupling 20 includes one or more couplings such as, for example, one or more spools, which are configured to directly couple theshaft 56 to theshaft 58 so that theshaft 56 directly drives theshaft 58, under conditions to be described below. In an exemplary embodiment, thecoupling 20 is omitted and theend portion 56 b of theshaft 56 is coupled to theend portion 58 a of theshaft 58 so that theshaft 56 directly drives theshaft 58, under conditions to be described below. In several exemplary embodiments, in addition to, or instead of one or more couplings such as, for example, one or more spools, thecoupling 20 includes one or more other types of devices and/or systems configured to directly couple theshaft 56 to theshaft 58 so that theshaft 56 directly drives theshaft 58. - In an exemplary embodiment, as illustrated in
FIG. 3 with continuing reference toFIGS. 1 and 2 , thegas generator 16 of theaeroderivative gas turbine 14 includes aninlet 60 and anoutlet 62 fluidicly coupled thereto, and ahousing 64. Acompressor 66 is disposed in thehousing 64 and is fluidicly coupled to theinlet 62. In an exemplary embodiment, thecompressor 66 includes one or more axial compressors. Acombustion chamber 68 including acombustor 70 is fluidicly coupled between thecompressor 66 and theoutlet 62. In several exemplary embodiments, theinlet 60 is fluidicly coupled to one or more lines, chutes, pipes, conduits or the like (not shown) via which air is adapted to be directed to theinlet 60, under conditions to be described below. - The
power turbine 18 of theaeroderivative gas turbine 14 includes acasing 72, anintake 74 fluidicly coupled to theoutlet 62 of thegas generator 16, and anexhaust 76 fluidicly coupled to theintake 74. Aturbine chamber 78 is fluidicly coupled between theintake 74 and theexhaust 76. A plurality of expansion stages 80 are disposed within theturbine chamber 78. In an exemplary embodiment, thepower turbine 18 weighs about 3,255 lbs. In several exemplary embodiments, theexhaust 76 is fluidicly coupled to one or more lines, chutes, pipes, conduits or the like (not shown) via which hot gas is adapted to be directed away from theexhaust 76, under conditions to be described below. - In an exemplary embodiment, as illustrated in
FIG. 4 with continuing reference toFIGS. 1-3 , the plurality of expansion stages 80 of thepower turbine 18 of theaeroderivative gas turbine 14 includes six (6) expansion stages, namely expansion stages 80 a, 80 b, 80 c, 80 d, 80 e and 80 f, each of which includes arotor blade 82 and astatic nozzle vane 84 disposed proximate thereto. Each of thestatic nozzle vanes 84 is coupled to thecasing 72 of thepower turbine 18. In an exemplary embodiment, each of thestatic nozzle vanes 84 is coupled to thecasing 72 of thepower turbine 18 by a separate annular shroud (not shown). Each of therotor blades 82 is coupled to, and extends radially outwardly away from, theshaft 56, and is adapted to rotate within thecasing 72, under conditions to be described below. In an exemplary embodiment, arotor 86 is coupled to theshaft 56, and each of therotor blades 82 is coupled to, and extends radially outwardly away from, therotor 86, thereby providing the coupling betweenblades 82 and theshaft 56. - In an exemplary embodiment, the
power turbine 18 is a low speed power turbine (LSPT) and the expansion stages 80 a, 80 b, 80 c, 80 d, 80 e and 80 f of thepower turbine 18 are configured to drive theshaft 56 and thus theshaft 58 at a rotational speed of about 3,600 rotations per minute (rpm), under conditions to be described below. In an exemplary embodiment, thepower turbine 18 is a low speed power turbine (LSPT) and the expansion stages 80 a, 80 b, 80 c, 80 d, 80 e and 80 f of thepower turbine 18 are configured to drive theshaft 56 and thus theshaft 58 at a rotational speed of about 3,600 rotations per minute (rpm), and to produce a power rating of less than about 55,000 horsepower (hp), under conditions to be described below. In an exemplary embodiment, thepower turbine 18 is a low speed power turbine (LSPT) and the expansion stages 80 a, 80 b, 80 c, 80 d, 80 e and 80 f of thepower turbine 18 are configured to drive theshaft 56 and thus theshaft 58 at a rotational speed of less than about 3,800 rotations per minute (rpm), and to produce a power rating of less than about 50,000 horsepower (hp), under conditions to be described below. In an exemplary embodiment, instead of six (6) expansion stages, the plurality of expansion stages 80 of thepower turbine 18 includes four (4) expansion stages. In several exemplary embodiments, instead of six (6) or four (4) expansion stages, the plurality of expansion stages 80 of thepower turbine 18 includes a different quantity of expansion stages. In an exemplary embodiment, thepower turbine 18 is configured to drive theshaft 56 and thus theshaft 58 at a rotational speed within a predetermined range of rotational speeds, under conditions to be described below. In an exemplary embodiment, thepower turbine 18 is configured to drive theshaft 56 and thus theshaft 58 at a rotational speed ranging from about 2,000 rpm to about 4,000 rpm, under conditions to be described below. In an exemplary embodiment, the maximum speed at which thepower turbine 18 is configured to drive theshaft 56 and thus theshaft 58 is about 3,780 rpm. In an exemplary embodiment, thepower turbine 18 has an ISO rating (15 degrees C.) of 45,100 horsepower, with a peak power of about 49,900 horsepower near −5 degrees C. In an exemplary embodiment, thepower turbine 18 has a power rating of less than about 55,000 horsepower (hp). In an exemplary embodiment, thepower turbine 18 has a power rating of less than about 50,000 horsepower (hp). In an exemplary embodiment, thepower turbine 18 is a modular unit of theaeroderivative gas turbine 14, and is permitted to be decoupled from, and re-coupled to, thegas generator 16 as a modular unit, under conditions to be described below. In an exemplary embodiment, thepower turbine 18 weighs about 3,255 lbs. - In an exemplary embodiment, the
aeroderivative gas turbine 14 has a relatively low weight. In an exemplary embodiment, thegas generator 16 has a weight ranging from about 4,590 lbs to about 7,625 lbs. In an exemplary embodiment, theaeroderivative gas turbine 14 has a weight ranging from about 7,845 lbs to about 10,880 lbs. In an exemplary embodiment, theaeroderivative gas turbine 14 is an LM2500+G4 LSPT aeroderivative gas turbine having a low speed power turbine (LSPT) with six (6) expansion stages, which type of aeroderivative gas turbine is commercially available from GE Aviation, Evendale, Ohio, USA, which is a subsidiary of the General Electric Company, Fairfield, Conn., USA. In an exemplary embodiment, theaeroderivative gas turbine 14 is another type of commercially available aeroderivative gas turbine. - In an exemplary embodiment, as illustrated in
FIG. 5 with continuing reference toFIGS. 1-4 , thecompressor 12 includes acasing 88, aninlet 90, and an outlet (not shown) fluidicly coupled to theinlet 90. A plurality ofimpellers 92 are coupled to theshaft 58 and are configured to rotate along withshaft 58, under conditions to be described below. In an exemplary embodiment, thecompressor 12 is configured to operate with a refrigerant flowing therethrough at a flow rate ranging from about 40,000 actual cubic feet per minute (ACFM) to about 70,000 ACFM, with theshaft 58 being directly driven by theshaft 56 of thepower turbine 18 of theaeroderivative gas turbine 14 at a rotational speed ranging from about 2,000 rpm to about 4,000 rpm, thereby pressurizing the refrigerant to a pressure upon discharge from thecompressor 12 ranging from about 30 pounds per square inch absolute (psia) to about 300 psia, under conditions to be described below. In an exemplary embodiment, thecompressor 12 is configured to operate with a refrigerant flowing therethrough at a flow rate ranging from about 40,000 actual cubic feet per minute (ACFM) to about 70,000 ACFM, with theshaft 58 being directly driven by theshaft 56 of thepower turbine 18 of theaeroderivative gas turbine 14 at a rotational speed of about 3,600 rpm, thereby pressurizing the refrigerant to a pressure upon discharge from thecompressor 12 ranging from about 30 psia to about 300 psia, under conditions to be described below. In an exemplary embodiment, thecompressor 12 is, includes, or is at least a part of, a centrifugal compressor. In an exemplary embodiment, thecompressor 12 is a DATUM® centrifugal compressor, which type of compressor is commercially available from the Dresser-Rand Company, Houston, Tex., USA. In an exemplary embodiment, thecompressor 12 is another type of commercially available centrifugal compressor. - In an exemplary embodiment, as illustrated in
FIG. 6 with continuing reference toFIGS. 1-5 , a method of operating thesystem 10 is generally referred to by thereference numeral 96 and includes receiving a fluid in a gas state into thesystem 10 instep 98, converting at least a portion of the fluid from the gas state into a liquid state instep 100 including subjecting the fluid to one or more cooling stages instep 102, and discharging the fluid from thesystem 10 instep 104. In an exemplary embodiment, the fluid in the gas state received into thesystem 10 in thestep 98 is natural gas, and at least a portion of the fluid is liquefied natural gas when the fluid is discharged from thesystem 10 in thestep 104. - In an exemplary embodiment, as illustrated in
FIG. 7 with continuing reference toFIGS. 1-6 , subjecting the fluid to one or more cooling stages in thestep 102 includes receiving the fluid into theheat exchanger 24 via theline 48 instep 106, removing heat from the fluid using theheat exchanger 24 instep 108, and discharging the fluid from theheat exchanger 24 via theline 50 instep 110. - In an exemplary embodiment, as illustrated in
FIG. 8 with continuing reference toFIGS. 1-7 , to remove heat from the fluid using theheat exchanger 24 in thestep 108, a refrigerant is circulated through theloop 38 instep 112, and heat is transferred from the fluid to the refrigerant instep 114 during the circulation of the refrigerant through theloop 38 in thestep 112. In thestep 112, the refrigerant continually flows through thecompressor 12, theline 30, thecondenser 26, theline 34, theexpansion valve 32, theline 36, theheat exchanger 24, and theline 28, as indicated by thearrows FIG. 1 ). In an exemplary embodiment, the refrigerant circulated through theloop 38 in thestep 112 is propane. In an exemplary embodiment, the refrigerant circulated through theloop 38 in thestep 112 is ethylene. In an exemplary embodiment, the refrigerant circulated through theloop 38 in thestep 112 is methane. In an exemplary embodiment, the refrigerant circulated through theloop 38 in thestep 112 is a gas with relatively high molecular weight. - In an exemplary embodiment, as illustrated in
FIG. 9 with continuing reference toFIGS. 1-8 , to transfer heat from the fluid to the refrigerant in thestep 114 during thestep 112, the refrigerant is compressed using thecompressor 12 instep 116, thereby pressurizing the refrigerant. Heat is removed from the refrigerant using thecondenser 26 instep 118, and the refrigerant is expanded using theexpansion valve 106 instep 120. Heat is transferred from the fluid flowing through theheat exchanger 24 and into the refrigerant flowing through theheat exchanger 24 instep 122. Thesteps loop 38 in thestep 114. In an exemplary embodiment, thesteps - In an exemplary embodiment, as illustrated in
FIG. 10 with continuing reference toFIGS. 1-9 , to compress the refrigerant using thecompressor 12 in thestep 116, the refrigerant is received into thecompressor 12 via theline 28 and theinlet 90 instep 124, theshaft 58 is directly driven by theaeroderivative gas turbine 14 to thereby rotate theimpellers 92 and pressurize the refrigerant instep 126, and the pressurized refrigerant is discharged from thecompressor 12 and into theline 30 instep 128. During each of thesteps step 126, the pressurized refrigerant is discharged from thecompressor 12 in thestep 128 at a pressure ranging from about 30 psia to about 300 psia. During thestep 126, theshaft 58 of thecompressor 12 is directly driven by theaeroderivative gas turbine 14 so that theshaft 58 rotates in place about theaxis 22 at a rotational speed ranging from about 2,000 rpm to about 4,000 rpm. In an exemplary embodiment, during thestep 126, theshaft 58 of thecompressor 12 is directly driven by theaeroderivative gas turbine 14 so that theshaft 58 rotates in place about theaxis 22 at a rotational speed of about 3,600 rpm. - In an exemplary embodiment, as illustrated in
FIG. 11 with continuing reference toFIGS. 1-10 , to directly drive theshaft 58 of thecompressor 12 using theaeroderivative gas turbine 14 in thestep 126, air flows into thegas generator 16 and thus theaeroderivative gas turbine 14 via theinlet 60 of thegas generator 16 instep 130, the air is compressed by thecompressor 66 of thegas generator 16 instep 132, and the compressed air is mixed with fuel and ignited to produce hot gas in thecombustion chamber 68 of thegas generator 16 instep 134. The hot gas exits thegas generator 16 via theoutlet 62 of thegas generator 16 and enters thepower turbine 18 via theinlet 74 of thepower turbine 18 instep 136. The hot gas is directed through the expansion stages 80 a, 80 b, 80 c, 80 d, 80 e and 80 f of thepower turbine 18 instep 138, thereby causing theshaft 56 of thepower turbine 18 to rotate in place about theaxis 22, which, in turn, directly drives theshaft 58 of thecompressor 12. More particularly, as the hot gas flows through each of thestages static nozzle vane 84 directs the hot gas against the correspondingrotor blade 82, thereby causing torque to be exerted on theshaft 56, thereby causing theshaft 56 to rotate in place about theaxis 22. Since theshaft 56 of thepower turbine 18 is directly coupled to theshaft 58 of thecompressor 12, the rotation of theshaft 56 in thestep 138 directly drives theshaft 58, causing theshaft 58 of thecompressor 12 to rotate during the rotation of theshaft 56 of thepower turbine 18 instep 140. As a result, during at least a portion of thestep 140, the respective rotational speeds of theshafts step 140, the rotational speed of each of theshafts step 140, the rotational speed of each of theshafts power turbine 18 and thus theaeroderivative gas turbine 14 via theexhaust 76 of thepower turbine 18 instep 142. In several exemplary embodiments, during at least a portion of the circulation of the refrigerant through theloop 38 in thestep 112, thesteps - The above-described direct coupling of the
shaft 56 of thepower turbine 18 of theaeroderivative gas turbine 14 to theshaft 58 of thecompressor 12 permits theshaft 56 to directly drive theshaft 58 in thestep 126. Since theshaft 56 directly drives theshaft 58 of thecompressor 12 in thestep 126, no speed-changing devices, such as, for example, gearboxes, gearing and/or similar mechanisms, are necessary for theshaft 56 to drive theshaft 58. The above-described direct coupling between theshafts compressor 12 provides additional liquefaction of the gas flowing into theheat exchanger 24 via theline 48 due to increased compressor throughput that arises from the recovery of friction power losses that are associated with a gearbox, which are typically on the order of about 1.5%. Further, the elimination of the need for a gearbox to drive thecompressor 12 provides incremental equipment reliability and availability due to the elimination of a major piece of rotating machinery. Still further, the elimination of the need for a gearbox to drive thecompressor 12 provides a reduced installation footprint by eliminating the gearbox from the line of rotating machinery. - In an exemplary calculated embodiment, as illustrated in
FIG. 12 with continuing reference toFIGS. 1-11 , exemplary calculations were conducted, the calculation results of which indicated that the use of the aeroderivative gas turbine 14 having the low speed power turbine (LSPT) 18 with the six (6) expansion stages 80 a, 80 b, 80 c, 80 d, 80 e and 80 f, which could be, for example, an LM2500+G4 LSPT aeroderivative gas turbine having a low speed power turbine (LSPT) with six (6) expansion stages, which type of aeroderivative gas turbine is commercially available from GE Aviation, Evendale, Ohio, USA, would provide more shaft power than the use of an aeroderivative gas turbine having a high speed power turbine (HSPT) with two (2) expansion stages, which could be, for example, an LM2500+G4 HSPT aeroderivative gas turbine having a high speed power turbine (HSPT) with two (2) expansion stages, which type of high speed power turbine may be a Dresser-Rand VECTRA® 40G4, which is commercially available from the Dresser-Rand Company, Houston, Tex., USA, or which type of high speed power turbine may be a General Electric PGT25+G4, which is commercially available from GE Oil and Gas, Florence, Italy; indeed, in an exemplary calculated embodiment, exemplary calculation results indicated that, with all other parameters being the same, the use of the low speed power turbine (LSPT) 18 having six (6) expansion stages 80 a, 80 b, 80 c, 80 d, 80 e and 80 f in the aeroderivative gas turbine 14 would offer more shaft power than a high speed power turbine (HSPT) having two (2) expansion stages in the aeroderivative gas turbine 14 at all site conditions for the conventional T48 control temperature of 1551 degrees F. These exemplary calculation results were unexpected. More particularly, as shown inFIG. 12 , exemplary calculations were conducted using the gas turbine manufacturer's performance cycle program in accordance with ASME PTC 22-2005, the calculation results of which indicated that, with the performance basis and all other parameters being the same, the use of the aeroderivative gas turbine 14 having the low speed power turbine (LSPT) 18 with the six (6) expansion stages 80 a, 80 b, 80 c, 80 d, 80 e and 80 f, which could be, for example, an LM2500+G4 LSPT aeroderivative gas turbine having a low speed power turbine (LSPT) with six (6) expansion stages, would offer more shaft power over a range of ambient temperatures, such as, for example, about 1.17% more shaft power at an ambient temperature ranging from about 22 to about 23 degrees C., about 1.57% more shaft power at an ambient temperature of about 27 degrees C., and about 1.38% more shaft power at an ambient temperature ranging from about 32 to about 33 degrees C., as compared to the use of an aeroderivative gas turbine having a high speed power turbine (HSPT) with two (2) expansion stages, which could be, for example, an LM2500+G4 HSPT aeroderivative gas turbine having a high speed power turbine (HSPT) with two (2) expansion stages. These exemplary calculation results were unexpected. Based on these unexpected exemplary calculation results, it was determined that, based on the same T48 temperature, an aeroderivative gas turbine having a low speed power turbine (LSPT) with six (6) expansion stages would provide more power than an aeroderivative gas turbine having a high speed power turbine (HSPT) with two (2) expansion stages. This determination, which was based on the exemplary calculation results, was unexpected. The performance basis and/or parameters for the exemplary calculations, the calculation results of which are shown inFIG. 12 , included the following: conventional T48 control temperature of 1551 degrees F.; 100-mm H2O inlet and exhaust pressure losses; 70% relative humidity; 1.012-barA barometer; dry, low emissions (DLE) combustor; design feed case fuel gas, 25 degrees C. supply; 100% shaft speed with 3,600 rpm for LSPT and 6,100 rpm for HSPT; and gear losses not considered. Based on the unexpected exemplary calculation results shown inFIG. 12 , additional exemplary calculations were conducted, the calculation results of which indicated that the incremental benefit in liquefied natural gas (LNG) production due to the selection of a low speed power turbine (LSPT) in theaeroderivative gas turbine 14 over a high speed (HSPT) in theaeroderivative gas turbine 14 would be about $176,000,000 net present value (NPV) with respect to operating income (OI); the shaft power increase shown inFIG. 12 would enable the amount of fluid converted into a liquid state, such as, for example, the amount of produced liquefied natural gas, to increase, resulting in an NPV of $176,000,000 with respect to operating income (OI). The assumptions for these exemplary calculations included the following: life cycle time of 25 years; net present value (NPV) based on 15% yearly discount; project cost of eight billion dollars; bank financial loan interest of 5%; gas price at entry of plant (at the fence) of 3.5 $ per MBtu; gas price at jetty (LNG price 75% of Henry Hubb) of 6.26 $ per MBtu; LNG price per ton of 327.7 $ per ton; LNG spot price of 655.3 $ per ton; plant size of 4.3 MTPA per line or LNG; and two lines of LNG. - In an exemplary embodiment, as illustrated in
FIG. 13A with continuing reference toFIGS. 1-12 , a method of performing maintenance on thegas liquefaction system 10 is generally referred to by thereference numeral 144 and includes decoupling theaeroderivative gas turbine 14, including thegas generator 16 and thepower turbine 18, as a modular unit from the remainder of thesystem 10 instep 146. Before, during and/or after thestep 146, maintenance is performed on at least theaeroderivative gas turbine 14 instep 148. Before, during and/or after thestep 148, theaeroderivative gas turbine 14 is re-coupled to the remainder of thesystem 10 as a modular unit instep 150. - In an exemplary embodiment, as illustrated in
FIG. 13B with continuing reference toFIGS. 1-13A , to decouple theaeroderivative gas turbine 14 from the remainder of thesystem 10 as a modular unit in thestep 146, theaeroderivative gas turbine 14 is decoupled as a modular unit. More particularly, theinlet 60 of thegas generator 16 of theaeroderivative gas turbine 14 is decoupled instep 152 from one or more lines, chutes, pipes, conduits or the like (not shown) via which air is directed to thegas generator 16. Before, during and/or after thestep 152, theexhaust 76 is decoupled instep 154 from one or more lines, chutes, pipes, conduits or the like (not shown) via which hot gas is directed away from thepower turbine 18. Before, during and/or after thesteps shaft 56 of thepower turbine 18 is decoupled from theshaft 58 of thecompressor 12 instep 156, which, in an exemplary embodiment, includes decoupling theend portion 56 b of theshaft 56 of thepower turbine 18 of theaeroderivative gas turbine 14 from theend portion 20 a of thecoupling 20. In several exemplary embodiments, thestep 156 includes one or more of the following: decoupling thecoupling 20 from theshaft 58 of thecompressor 12; decoupling theshaft 56 of thepower turbine 18 from thecoupling 20; decoupling theshaft 56 of thepower turbine 18 from theshaft 58 of thecompressor 12; decoupling theend portion 20 b from theend portion 58 a; and decoupling theend portion 56 b from theend portion 58 a. In several exemplary embodiments, before, during and/or after thesteps 146 and/or 148, thepower turbine 18 is decoupled from thegas generator 16 as a modular unit. - In an exemplary embodiment, to re-couple the
aeroderivative gas turbine 14 to the remainder of thesystem 10 in thestep 150 of themethod 144, theinlet 60 of thegas generator 16 of theaeroderivative gas turbine 14 is re-coupled to one or more lines, chutes, pipes, conduits or the like (not shown) via which air is directed to thegas generator 16, theexhaust 76 is re-coupled to one or more lines, chutes, pipes, conduits or the like (not shown) via which hot gas is directed away from thepower turbine 18, theshaft 56 of thepower turbine 18 is re-coupled to theshaft 58 of thecompressor 12, which, in an exemplary embodiment, includes re-coupling theend portion 56 b of theshaft 56 of thepower turbine 18 of theaeroderivative gas turbine 14 to theend portion 20 a of thecoupling 20. In several exemplary embodiments, re-coupling theshaft 56 to theshaft 58 includes one or more of the following: re-coupling thecoupling 20 to theshaft 58 of thecompressor 12; re-coupling theshaft 56 of thepower turbine 18 to thecoupling 20; re-coupling theshaft 56 of thepower turbine 18 to theshaft 58 of thecompressor 12; re-coupling theend portion 20 b to theend portion 58 a; and re-coupling theend portion 56 b to theend portion 58 a. In several exemplary embodiments, before, during and/or after thesteps power turbine 18 is re-coupled to thegas generator 16 as a modular unit. - In an exemplary embodiment, as illustrated in
FIG. 13C with continuing reference toFIGS. 1-13B , a method of performing maintenance on thegas liquefaction system 10 is generally referred to by thereference numeral 157 and includes decoupling theaeroderivative gas turbine 14, including thegas generator 16 and thepower turbine 18, as a modular unit from the remainder of thesystem 10 instep 157 a. Before, during and/or after thestep 157 a, a spare aeroderivative gas turbine, which is substantially similar to theaeroderivative gas turbine 14, is coupled to the remainder of thesystem 10 as a modular unit instep 157 b, after which thesystem 10 is operated instep 157 c in accordance with the foregoing. Before, during and/or after thesteps aeroderivative gas turbine 14 instep 157 d. Before, during and/or after thestep 157 d, the spare aeroderivative gas turbine is decoupled from the remainder of thesystem 10 instep 157 e. Before, during and/or after thesteps 157 d and/or 157 e, theaeroderivative gas turbine 14 is re-coupled to the remainder of thesystem 10 as a modular unit instep 157 f. Thestep 157 a is substantially similar to thestep 146 and therefore will not be described in detail. Thestep 157 b is substantially similar to thestep 150 and therefore will not be described in detail, except that the spare aeroderivative gas turbine is coupled to the remainder of thesystem 10 in thestep 157 b, rather than theaeroderivative gas turbine 14. Thestep 157 c is substantially similar to themethod 96 and therefore will not be described in detail, except that thesystem 10 is operated with the spare aeroderivative gas turbine in thestep 157 c, rather than theaeroderivative gas turbine 14. Thestep 157 d is substantially similar to thestep 148 and therefore will not be described in detail. Thestep 157 e is substantially similar to either thestep 146 or thestep 157 a and therefore will not be described in detail, except that the spare aeroderivative gas turbine is decoupled from the remainder of thesystem 10 in thestep 157 e, rather theaeroderivative gas turbine 14. Thestep 157 f is substantially similar to thestep 150 and therefore will not be described in detail. - The relatively low weight of the
aeroderivative gas turbine 14, and the decoupling of theaeroderivative gas turbine 14 from the remainder of thesystem 10 as a modular unit in thestep aeroderivative gas turbine 14 readily removable from thecompressor 12 in the form of a complete gas turbine. The modularity of theaeroderivative gas turbine 14, with respect to at least thecompressor 12, results in a substantial reduction in “down time” in that, during routine maintenance, theaeroderivative gas turbine 14 and/or its components such as thegas generator 16 and/or thepower turbine 18 do not need to be disassembled in place in thesystem 10 and/or while theaeroderivative gas turbine 14 is coupled to thecompressor 12. In an exemplary embodiment, the modularity of theaeroderivative gas turbine 14, i.e., the ability to decouple theaeroderivative gas turbine 14 from the remainder of thesystem 10 as a modular unit in thestep system 10. - In an exemplary embodiment, as illustrated in
FIG. 14 with continuing reference toFIGS. 1-13C , exemplary calculations were conducted, the calculation results of which indicated that the use of the aeroderivative gas turbine 14 having the low speed power turbine (LSPT) 18 with the six (6) expansion stages 80 a, 80 b, 80 c, 80 d, 80 e and 80 f, which could be, for example, an LM2500+G4 LSPT aeroderivative gas turbine having a low speed power turbine (LSPT) with six (6) expansion stages, which type of aeroderivative gas turbine is commercially available from GE Aviation, Evendale, Ohio, USA, would reduce the cost associated with cumulative loss of production as a result of “down time” for routine and/or scheduled maintenance of at least the aeroderivative gas turbine 14, that is, the cost associated with not being able to convert as much of the fluid as possible into a liquid state in the step 100 of the method 96 because the aeroderivative gas turbine 14 and the compressor 12 are inoperable due to routine and/or scheduled maintenance, than the use of an aeroderivative gas turbine having a high speed power turbine (HSPT) with two (2) expansion stages, which could be, for example, an LM2500+G4 HSPT aeroderivative gas turbine having a high speed power turbine (HSPT) with two (2) expansion stages, which type of high speed power turbine may be a Dresser-Rand VECTRA® 40G4, which is commercially available from the Dresser-Rand Company, Houston, Tex., USA, or which type of high speed power turbine may be a General Electric PGT25+G4, which is commercially available from GE Oil and Gas, Florence, Italy. As shown inFIG. 14 , exemplary calculations were conducted, the calculation results of which indicated that, with the performance basis and all other parameters being the same, the use of theaeroderivative gas turbine 14 having the low speed power turbine (LSPT) 18 with the six (6) expansion stages 80 a, 80 b, 80 c, 80 d, 80 e and 80 f, which could be, for example, an LM2500+G4 LSPT aeroderivative gas turbine having a low speed power turbine (LSPT) with six (6) expansion stages, in accordance with themethod 157, would provide a cost savings associated with cumulative loss of production as a result of “down time” for routine and/or scheduled maintenance over the operational life of theaeroderivative gas turbine 14 of, for example, about $10,000,000 after an operational time period of about eight years, and about $27,000,000 after an operational time period of about twenty five years, as compared to the use of an aeroderivative gas turbine having a high speed power turbine (HSPT) with two (2) expansion stages, which could be, for example, an LM2500+G4 HSPT aeroderivative gas turbine having a high speed power turbine (HSPT) with two (2) expansion stages. These exemplary calculation results were unexpected. The cost savings shown inFIG. 14 are based on, inter alia, the scheduled maintenance for both the LM2500+G4 LSPT aeroderivative gas turbine and the LM2500+G4 HSPT aeroderivative gas turbine, plant nominal capacity, and incremental sales rather than operating income (OI). The shorter maintenance schedule of theaeroderivative gas turbine 14 having the low speed power turbine (LSPT) 18 with the six (6) expansion stages 80 a, 80 b, 80 c, 80 d, 80 e and 80 f would provide the exemplary calculated cost savings shown inFIG. 14 . More particularly, the execution of themethod 157 greatly reduces the amount of days of “down time” of theaeroderivative gas turbine 14 and thecompressor 12. The exemplary calculated cost savings shown inFIG. 14 assume that routine and/or scheduled maintenance performed on at least theaeroderivative gas turbine 14, in accordance with themethod 157, would take no more than about two days. - In an exemplary embodiment, as illustrated in
FIG. 15 with continuing reference toFIGS. 1-14 , a system is generally referred to by thereference numeral 158 and includes several parts of thesystem 10, which parts are given the same reference numerals. As shown inFIG. 15 , thesystem 158 further includes acompressor 160 directly coupled to thecompressor 12 via acoupling 162. Thecompressor 160 is fluidicly coupled between theheat exchanger 24 and acondenser 164 vialines expansion valve 170, is fluidicly coupled between thecondenser 164 and theheat exchanger 24 vialines heat exchanger 24, thecompressor 160, thecondenser 164, theexpansion valve 170, and thelines loop 176, through which a refrigerant is adapted to circulate in a direction indicated byarrows compressor 12 in thesystem 158 is a double flow compressor, and thecompressor 160 is a single flow compressor. - In an exemplary embodiment, the operation of the
system 158 is similar to themethod 96 of operation of thesystem 10 and will not be described in detail, except that theaeroderivative gas turbine 14 also drives thecompressor 160, in addition to driving thecompressor 12; thestep 112 includes circulating refrigerant through theloop 176, in addition to circulating refrigerant through theloop 38; and thestep 114 includes transferring heat from the fluid, which flows through theline 48, theheat exchanger 24, and theline 50, into the refrigerant circulating through theloop 176, in addition to the refrigerant circulating through theloop 38. In an exemplary embodiment, maintenance is performed on thesystem 158 in a manner substantially similar to themethod 144. In an exemplary embodiment, maintenance is performed on thesystem 158 in a manner substantially similar to themethod 157. - In several exemplary embodiments, instead of, or in addition to one or more of the
compressors aeroderivative gas turbine 14 in thesystems 10 and/or 158. - In several exemplary embodiments, one or more waste heat recovery cycles and/or systems are operably coupled to the
aeroderivative gas turbine 14. In several exemplary embodiments, one or more waste heat recovery cycles and/or systems are operably coupled between theaeroderivative gas turbine 14 and theheat exchanger 24. In several exemplary embodiments, one or more waste heat recovery cycles and/or systems are operably coupled to theaeroderivative gas turbine 14 and one or more other components of thesystem 10 such as, for example, one or more of theheat exchanger 24, theline 48, theline 50, and/or any combination thereof. In several exemplary embodiments, one or more waste heat recovery cycles and/or systems are operably coupled to theaeroderivative gas turbine 14 and one or more other components of thesystem 158 such as, for example, one or more of theheat exchanger 24, theline 48, theline 50, and/or any combination thereof. - A system has been described that includes a compressor system including a compressor through which a refrigerant is adapted to flow, the compressor including a first shaft; and an aeroderivative gas turbine for driving the compressor, the aeroderivative gas turbine including a gas generator; and a low speed power turbine coupled to the gas generator, the low speed power turbine including a second shaft directly coupled to the first shaft of the compressor for directly driving the first shaft; wherein the respective rotational speeds of the first and second shafts are substantially equal. In an exemplary embodiment, the system includes a gas liquefaction system for converting at least a portion of a fluid from a gas state into a liquid state, the fluid in the gas state including natural gas, the fluid in the liquid state including liquefied natural gas, the gas liquefaction system including one or more cooling stages including the refrigerant; and a loop through which the refrigerant is adapted to circulate, the loop including a heat exchanger for transferring heat out of the fluid and into the refrigerant; the compressor of the compressor system for pressurizing the refrigerant; a condenser for transferring heat out of the refrigerant; and an expansion element for expanding the refrigerant; wherein the aeroderivative gas turbine is coupled to the compressor as a modular unit; wherein the low speed power turbine is coupled to the gas generator as a modular unit; wherein the compressor comprises a centrifugal compressor; wherein the refrigerant flows through the centrifugal compressor at a flow rate ranging from about 40,000 actual cubic feet per minute to about 70,000 actual cubic feet per minute; wherein the compressor pressurizes the refrigerant so that the pressurized refrigerant is discharged from the compressor at a pressure ranging from about 30 pounds per square inch absolute to about 300 pounds per square inch absolute; wherein the low speed power turbine includes at least six expansion stages for driving the second shaft; wherein the at least six expansion stages drives the second shaft so that the low speed power turbine has a power rating of less than about 55,000 horsepower; wherein the first and second shafts are generally axially aligned; and wherein the rotational speed of the first and second shafts ranges from about 2,000 revolutions per minute to about 4,000 revolutions per minute. In an exemplary embodiment, the first and second shafts are generally axially aligned; and wherein the rotational speed of the first and second shafts ranges from about 2,000 revolutions per minute to about 4,000 revolutions per minute. In an exemplary embodiment, the compressor comprises a centrifugal compressor configured so that the refrigerant is adapted to flow through the centrifugal compressor at a flow rate ranging from about 40,000 actual cubic feet per minute to about 70,000 actual cubic feet per minute; and wherein the centrifugal compressor is configured to pressurize the refrigerant so that the pressurized refrigerant is discharged from the centrifugal compressor at a pressure ranging from about 30 pounds per square inch absolute to about 300 pounds per square inch absolute. In an exemplary embodiment, the low speed power turbine includes at least six expansion stages for driving the second shaft; and wherein the at least six expansion stages drives the second shaft so that the low speed power turbine has a power rating of less than about 55,000 horsepower. In an exemplary embodiment, the aeroderivative gas turbine is coupled to the compressor as a modular unit; and wherein the low speed power turbine is coupled to the gas generator as a modular unit. In an exemplary embodiment, the system includes a gas liquefaction system for converting at least a portion of a fluid from a gas state into a liquid state, the fluid in the gas state including natural gas, the fluid in the liquid state including liquefied natural gas, the gas liquefaction system including one or more cooling stages including the refrigerant; and a loop through which the refrigerant is adapted to circulate, the loop including a heat exchanger for transferring heat out of the fluid and into the refrigerant; the compressor of the compressor system for pressurizing the refrigerant; a condenser for transferring heat out of the refrigerant; and an expansion element for expanding the refrigerant.
- A method has been described that includes providing a compressor including a first shaft; providing an aeroderivative gas turbine including a power turbine including a second shaft; directly coupling the second shaft of the power turbine to the first shaft of the compressor; circulating a refrigerant through the compressor; and pressurizing the refrigerant with the compressor, including directly driving the compressor using the aeroderivative gas turbine, including rotating the first shaft of the power turbine at a first rotational speed; and rotating the second shaft of the compressor at a second rotational speed; wherein the first and second rotational speeds are substantially equal. In an exemplary embodiment, the method includes converting at least a portion of a fluid from a gas state into a liquid state, the fluid in the gas state including natural gas, the fluid in the liquid state including liquefied natural gas; wherein converting at least a portion of the fluid from the gas state into the liquid state includes transferring heat from the fluid and into the refrigerant; wherein the compressor comprises a centrifugal compressor; wherein the power turbine is a low speed power turbine including at least six expansion stages; wherein circulating the refrigerant through the compressor includes circulating the refrigerant through the compressor at a flow rate ranging from about 40,000 actual cubic feet per minute to about 70,000 actual cubic feet per minute; wherein pressurizing the refrigerant with the compressor includes pressurizing the refrigerant with the compressor so that the pressurized refrigerant is discharged from the compressor at a pressure ranging from about 30 pounds per square inch absolute to about 300 pounds per square inch absolute; wherein rotating the first shaft of the power turbine at the first rotational speed includes driving the first shaft using the at least six expansion stages so that the low speed power turbine has a power rating of less than about 55,000 horsepower; wherein the first and second shafts are generally axially aligned; and wherein each of the first and second rotational speeds ranges from about 2,000 revolutions per minute to about 4,000 revolutions per minute. In an exemplary embodiment, the method includes converting at least a portion of a fluid from a gas state into a liquid state, the fluid in the gas state including natural gas, the fluid in the liquid state including liquefied natural gas; wherein converting at least a portion of the fluid from the gas state into the liquid state includes transferring heat from the fluid and into the refrigerant. In an exemplary embodiment, the compressor comprises a centrifugal compressor; wherein circulating the refrigerant through the compressor includes circulating the refrigerant through the compressor at a flow rate ranging from about 40,000 actual cubic feet per minute to about 70,000 actual cubic feet per minute; and wherein pressurizing the refrigerant with the compressor includes pressurizing the refrigerant with the compressor so that the pressurized refrigerant is discharged from the compressor at a pressure ranging from about 30 pounds per square inch absolute to about 300 pounds per square inch absolute. In an exemplary embodiment, the power turbine is a low speed power turbine including at least six expansion stages; and wherein rotating the first shaft of the power turbine at the first rotational speed includes driving the first shaft using the at least six expansion stages so that the low speed power turbine has a power rating of less than about 55,000 horsepower. In an exemplary embodiment, the method includes decoupling the aeroderivative gas turbine from the compressor as a modular unit; performing maintenance on at least the aeroderivative gas turbine; and re-coupling the aeroderivative gas turbine to the compressor as a modular unit. In an exemplary embodiment, decoupling the aeroderivative gas turbine from the compressor as a modular unit includes decoupling the first shaft of the power turbine from the second shaft of the compressor; and wherein re-coupling the aeroderivative gas turbine to the compressor as a modular unit includes re-coupling the first shaft of the power turbine to the second shaft of the compressor. In an exemplary embodiment, the first and second shafts are generally axially aligned; and wherein each of the first and second rotational speeds ranges from about 2,000 revolutions per minute to about 4,000 revolutions per minute.
- A method has been described that includes providing a gas liquefaction system including a compressor and an aeroderivative gas turbine coupled thereto, the aeroderivative gas turbine including a gas generator and a power turbine coupled thereto; decoupling the aeroderivative gas turbine from a remainder of the gas liquefaction system as a modular unit; performing maintenance on at least the aeroderivative gas turbine; and re-coupling the aeroderivative gas turbine to the remainder of the gas liquefaction system as a modular unit after decoupling the aeroderivative gas turbine from the remainder of the gas liquefaction system as a modular unit. In an exemplary embodiment, the aeroderivative gas turbine includes an inlet for receiving air into the gas generator; wherein the power turbine includes an exhaust for discharging gas from the power turbine, wherein the exhaust is fluidicly coupled to the inlet when the aeroderivative gas turbine is in the form of the modular unit, and a first shaft; wherein the compressor includes a second shaft directly coupled to the first shaft of the power turbine when the aeroderivative gas turbine is coupled to the compressor; and wherein decoupling the aeroderivative gas turbine from the remainder of the gas liquefaction system as a modular unit includes decoupling the inlet of the gas generator from means via which the air is adapted to be directed to the gas generator; decoupling the exhaust of the power turbine from means via which the gas is adapted to be directed away from the power turbine; and decoupling the first shaft from the second shaft. In an exemplary embodiment, re-coupling the aeroderivative gas turbine to the remainder of the gas liquefaction system as a modular unit includes re-coupling the inlet of the gas generator to the means via which the air is adapted to be directed to the gas generator; re-coupling the exhaust of the power turbine to the means via which the gas is adapted to be directed away from the power turbine; and re-coupling the first shaft to the second shaft. In an exemplary embodiment, the method includes converting at least a portion of a fluid from a gas state into a liquid state, the fluid in the gas state including natural gas, the fluid in the liquid state including liquefied natural gas; wherein converting at least a portion of the fluid from the gas state to the liquid state includes subjecting the fluid to one or more cooling stages, including receiving fluid into a heat exchanger fluidicly coupled to the compressor; removing heat from the fluid using the heat exchanger; and discharging the fluid from the heat exchanger; and wherein removing heat from the fluid using the heat exchanger includes circulating a refrigerant through a loop, the loop including the heat exchanger and the compressor; and transferring heat from the fluid and to the refrigerant during circulating the refrigerant through the loop, including transferring heat from the fluid and to the refrigerant using the heat exchanger; and pressurizing the refrigerant with the compressor, including directly driving the compressor using the aeroderivative gas turbine, including rotating the first shaft of the power turbine at a first rotational speed; and rotating the second shaft of the compressor at a second rotational speed; wherein the first and second rotational speeds are substantially equal. In an exemplary embodiment, the method includes coupling a spare aeroderivative gas turbine to the remainder of the gas liquefaction system as a modular unit; operating the gas liquefaction system with the spare aeroderivative gas turbine; and decoupling the spare aeroderivative gas turbine from the remainder of the gas liquefaction system as a modular unit.
- It is understood that variations may be made in the foregoing without departing from the scope of the disclosure. In several exemplary embodiments, the elements and teachings of the various illustrative exemplary embodiments may be combined in whole or in part in some or all of the illustrative exemplary embodiments. In addition, one or more of the elements and teachings of the various illustrative exemplary embodiments may be omitted, at least in part, and/or combined, at least in part, with one or more of the other elements and teachings of the various illustrative embodiments.
- Any spatial references such as, for example, “upper,” “lower,” “above,” “below,” “between,” “bottom,” “vertical,” “horizontal,” “angular,” “upwards,” “downwards,” “side-to-side,” “left-to-right,” “left,” “right,” “right-to-left,” “top-to-bottom,” “bottom-to-top,” “top,” “bottom,” “bottom-up,” “top-down,” etc., are for the purpose of illustration only and do not limit the specific orientation or location of the structure described above.
- In several exemplary embodiments, while different steps, processes, and procedures are described as appearing as distinct acts, one or more of the steps, one or more of the processes, and/or one or more of the procedures may also be performed in different orders, simultaneously and/or sequentially. In several exemplary embodiments, the steps, processes and/or procedures may be merged into one or more steps, processes and/or procedures. In several exemplary embodiments, one or more of the operational steps in each embodiment may be omitted. Moreover, in some instances, some features of the present disclosure may be employed without a corresponding use of the other features. Moreover, one or more of the above-described embodiments and/or variations may be combined in whole or in part with any one or more of the other above-described embodiments and/or variations. In the claims, any means-plus-function clauses are intended to cover the structures described herein as performing the recited function and not only structural equivalents, but also equivalent structures.
- The foregoing has outlined features of several embodiments so that those skilled in the art may better understand the detailed description that follows. Those skilled in the art should appreciate that they may readily use the present disclosure as a basis for designing or modifying other processes and structures for carrying out the same purposes and/or achieving the same advantages of the embodiments introduced herein. Those skilled in the art should also realize that such equivalent constructions do not depart from the spirit and scope of the present disclosure, and that they may make various changes, substitutions and alterations herein without departing from the spirit and scope of the present disclosure.
Claims (20)
1. A system for compressing a refrigerant, the system comprising:
a compressor system comprising:
a compressor through which the refrigerant is adapted to flow, the compressor comprising a first shaft; and
an aeroderivative gas turbine for driving the compressor, the aeroderivative gas turbine comprising:
a gas generator; and
a low speed power turbine coupled to the gas generator, the low speed power turbine comprising a second shaft directly coupled to the first shaft of the compressor for directly driving the first shaft;
wherein the respective rotational speeds of the first and second shafts are substantially equal.
2. The system of claim 1 , further comprising:
a gas liquefaction system for converting at least a portion of a fluid from a gas state into a liquid state, the fluid in the gas state comprising natural gas, the fluid in the liquid state comprising liquefied natural gas, the gas liquefaction system comprising:
one or more cooling stages comprising:
the refrigerant; and
a loop through which the refrigerant is adapted to circulate, the loop comprising:
a heat exchanger for transferring heat out of the fluid and into the refrigerant;
the compressor of the compressor system for pressurizing the refrigerant;
a condenser for transferring heat out of the refrigerant; and
an expansion element for expanding the refrigerant;
wherein the aeroderivative gas turbine is coupled to the compressor as a modular unit;
wherein the low speed power turbine is coupled to the gas generator as a modular unit;
wherein the compressor comprises a centrifugal compressor;
wherein the refrigerant flows through the centrifugal compressor at a flow rate ranging from about 40,000 actual cubic feet per minute to about 70,000 actual cubic feet per minute;
wherein the compressor pressurizes the refrigerant so that the pressurized refrigerant is discharged from the compressor at a pressure ranging from about 30 pounds per square inch absolute to about 300 pounds per square inch absolute;
wherein the low speed power turbine comprises at least six expansion stages for driving the second shaft;
wherein the at least six expansion stages drives the second shaft so that the low speed power turbine has a power rating of less than about 55,000 horsepower;
wherein the first and second shafts are generally axially aligned; and
wherein the rotational speed of the first and second shafts ranges from about 2,000 revolutions per minute to about 4,000 revolutions per minute.
3. The system of claim 1 , wherein the first and second shafts are generally axially aligned; and
wherein the rotational speed of the first and second shafts ranges from about 2,000 revolutions per minute to about 4,000 revolutions per minute.
4. The system of claim 1 , wherein the compressor comprises a centrifugal compressor configured so that the refrigerant is adapted to flow through the centrifugal compressor at a flow rate ranging from about 40,000 actual cubic feet per minute to about 70,000 actual cubic feet per minute; and
wherein the centrifugal compressor is configured to pressurize the refrigerant so that the pressurized refrigerant is discharged from the centrifugal compressor at a pressure ranging from about 30 pounds per square inch absolute to about 300 pounds per square inch absolute.
5. The system of claim 1 , wherein the low speed power turbine comprises at least six expansion stages for driving the second shaft; and
wherein the at least six expansion stages drives the second shaft so that the low speed power turbine has a power rating of less than about 55,000 horsepower.
6. The system of claim 1 , wherein the aeroderivative gas turbine is coupled to the compressor as a modular unit; and
wherein the low speed power turbine is coupled to the gas generator as a modular unit.
7. The system of claim 1 , further comprising:
a gas liquefaction system for converting at least a portion of a fluid from a gas state into a liquid state, the fluid in the gas state comprising natural gas, the fluid in the liquid state comprising liquefied natural gas, the gas liquefaction system comprising:
one or more cooling stages comprising:
the refrigerant; and
a loop through which the refrigerant is adapted to circulate, the loop comprising:
a heat exchanger for transferring heat out of the fluid and into the refrigerant;
the compressor of the compressor system for pressurizing the refrigerant;
a condenser for transferring heat out of the refrigerant; and
an expansion element for expanding the refrigerant.
8. A method of compressing a refrigerant, the method comprising:
providing a compressor having a first shaft;
providing an aeroderivative gas turbine having a power turbine that includes a second shaft;
directly coupling the second shaft of the power turbine to the first shaft of the compressor;
circulating the refrigerant through the compressor; and
pressurizing the refrigerant with the compressor, comprising:
directly driving the compressor using the aeroderivative gas turbine, comprising:
rotating the first shaft of the power turbine at a first rotational speed; and
rotating the second shaft of the compressor at a second rotational speed;
wherein the first and second rotational speeds are substantially equal.
9. The method of claim 8 , further comprising:
converting at least a portion of a fluid from a gas state into a liquid state, the fluid in the gas state comprising natural gas, the fluid in the liquid state comprising liquefied natural gas;
wherein converting at least a portion of the fluid from the gas state into the liquid state comprises transferring heat from the fluid and into the refrigerant;
wherein the compressor comprises a centrifugal compressor;
wherein the power turbine is a low speed power turbine comprising at least six expansion stages;
wherein circulating the refrigerant through the compressor comprises circulating the refrigerant through the compressor at a flow rate ranging from about 40,000 actual cubic feet per minute to about 70,000 actual cubic feet per minute;
wherein pressurizing the refrigerant with the compressor comprises pressurizing the refrigerant with the compressor so that the pressurized refrigerant is discharged from the compressor at a pressure ranging from about 30 pounds per square inch absolute to about 300 pounds per square inch absolute;
wherein rotating the first shaft of the power turbine at the first rotational speed comprises driving the first shaft using the at least six expansion stages so that the low speed power turbine has a power rating of less than about 55,000 horsepower;
wherein the first and second shafts are generally axially aligned; and
wherein each of the first and second rotational speeds ranges from about 2,000 revolutions per minute to about 4,000 revolutions per minute.
10. The method of claim 8 , further comprising:
converting at least a portion of a fluid from a gas state into a liquid state, the fluid in the gas state comprising natural gas, the fluid in the liquid state comprising liquefied natural gas;
wherein converting at least a portion of the fluid from the gas state into the liquid state comprises transferring heat from the fluid and into the refrigerant.
11. The method of claim 8 , wherein the compressor comprises a centrifugal compressor;
wherein circulating the refrigerant through the compressor comprises circulating the refrigerant through the compressor at a flow rate ranging from about 40,000 actual cubic feet per minute to about 70,000 actual cubic feet per minute; and
wherein pressurizing the refrigerant with the compressor comprises pressurizing the refrigerant with the compressor so that the pressurized refrigerant is discharged from the compressor at a pressure ranging from about 30 pounds per square inch absolute to about 300 pounds per square inch absolute.
12. The method of claim 8 , wherein the power turbine is a low speed power turbine comprising at least six expansion stages; and
wherein rotating the first shaft of the power turbine at the first rotational speed comprises driving the first shaft using the at least six expansion stages so that the low speed power turbine has a power rating of less than about 55,000 horsepower.
13. The method of claim 8 , further comprising:
decoupling the aeroderivative gas turbine from the compressor as a modular unit;
performing maintenance on at least the aeroderivative gas turbine; and
re-coupling the aeroderivative gas turbine to the compressor as a modular unit.
14. The method of claim 13 , wherein decoupling the aeroderivative gas turbine from the compressor as a modular unit comprises decoupling the first shaft of the power turbine from the second shaft of the compressor; and
wherein re-coupling the aeroderivative gas turbine to the compressor as a modular unit comprises re-coupling the first shaft of the power turbine to the second shaft of the compressor.
15. The method of claim 8 , wherein the first and second shafts are generally axially aligned; and
wherein each of the first and second rotational speeds ranges from about 2,000 revolutions per minute to about 4,000 revolutions per minute.
16. A method of performing maintenance on a gas liquefaction system, the method comprising:
providing the gas liquefaction system comprising a compressor and an aeroderivative gas turbine coupled thereto, the aeroderivative gas turbine comprising a gas generator and a power turbine coupled thereto;
decoupling the aeroderivative gas turbine from a remainder of the gas liquefaction system as a modular unit;
performing maintenance on at least the aeroderivative gas turbine; and
re-coupling the aeroderivative gas turbine to the remainder of the gas liquefaction system as a modular unit after decoupling the aeroderivative gas turbine from the remainder of the gas liquefaction system as a modular unit.
17. The method of claim 16 , wherein the aeroderivative gas turbine comprises an inlet for receiving air into the gas generator;
wherein the power turbine comprises:
an exhaust for discharging gas from the power turbine, wherein the exhaust is fluidicly coupled to the inlet when the aeroderivative gas turbine is in the form of the modular unit, and
a first shaft;
wherein the compressor comprises a second shaft directly coupled to the first shaft of the power turbine when the aeroderivative gas turbine is coupled to the compressor; and
wherein decoupling the aeroderivative gas turbine from the remainder of the gas liquefaction system as a modular unit comprises:
decoupling the inlet of the gas generator from means via which the air is adapted to be directed to the gas generator;
decoupling the exhaust of the power turbine from means via which the gas is adapted to be directed away from the power turbine; and
decoupling the first shaft from the second shaft.
18. The method of claim 17 , wherein re-coupling the aeroderivative gas turbine to the remainder of the gas liquefaction system as a modular unit comprises:
re-coupling the inlet of the gas generator to the means via which the air is adapted to be directed to the gas generator;
re-coupling the exhaust of the power turbine to the means via which the gas is adapted to be directed away from the power turbine; and
re-coupling the first shaft to the second shaft.
19. The method of claim 18 , further comprising:
converting at least a portion of a fluid from a gas state into a liquid state, the fluid in the gas state comprising natural gas, the fluid in the liquid state comprising liquefied natural gas;
wherein converting at least a portion of the fluid from the gas state to the liquid state comprises:
subjecting the fluid to one or more cooling stages, comprising:
receiving fluid into a heat exchanger fluidicly coupled to the compressor;
removing heat from the fluid using the heat exchanger; and
discharging the fluid from the heat exchanger;
and
wherein removing heat from the fluid using the heat exchanger comprises:
circulating a refrigerant through a loop, the loop comprising the heat exchanger and the compressor; and
transferring heat from the fluid and to the refrigerant during circulating the refrigerant through the loop, comprising:
transferring heat from the fluid and to the refrigerant using the heat exchanger; and
pressurizing the refrigerant with the compressor, comprising:
directly driving the compressor using the aeroderivative gas turbine, comprising:
rotating the first shaft of the power turbine at a first rotational speed; and
rotating the second shaft of the compressor at a second rotational speed;
wherein the first and second rotational speeds are substantially equal.
20. The method of claim 16 , further comprising:
coupling a spare aeroderivative gas turbine to the remainder of the gas liquefaction system as a modular unit;
operating the gas liquefaction system with the spare aeroderivative gas turbine; and
decoupling the spare aeroderivative gas turbine from the remainder of the gas liquefaction system as a modular unit.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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US12/746,131 US20100293967A1 (en) | 2007-12-07 | 2008-12-05 | Compressor system and method for gas liquefaction system |
Applications Claiming Priority (3)
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PCT/US2008/085640 WO2009073838A1 (en) | 2007-12-07 | 2008-12-05 | Compressor system and method for gas liquefaction system |
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Also Published As
Publication number | Publication date |
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EP2336693A2 (en) | 2011-06-22 |
EP2217869A1 (en) | 2010-08-18 |
KR20100105640A (en) | 2010-09-29 |
JP2011506895A (en) | 2011-03-03 |
KR101259238B1 (en) | 2013-04-29 |
CA2708154A1 (en) | 2009-06-11 |
JP2015129635A (en) | 2015-07-16 |
EP2336693A3 (en) | 2015-07-01 |
BRPI0820933B1 (en) | 2020-09-24 |
WO2009073838A1 (en) | 2009-06-11 |
AU2008333840B2 (en) | 2012-11-15 |
BRPI0820933A2 (en) | 2016-05-03 |
EP2217869A4 (en) | 2015-06-24 |
AU2008333840A1 (en) | 2009-06-11 |
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