US2729938A - Combustion chamber crossover tube - Google Patents
Combustion chamber crossover tube Download PDFInfo
- Publication number
- US2729938A US2729938A US207934A US20793451A US2729938A US 2729938 A US2729938 A US 2729938A US 207934 A US207934 A US 207934A US 20793451 A US20793451 A US 20793451A US 2729938 A US2729938 A US 2729938A
- Authority
- US
- United States
- Prior art keywords
- tube
- flame
- tubes
- sleeve
- crossover
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
- F23R3/48—Flame tube interconnectors, e.g. cross-over tubes
Description
Jan. 10, 1956 c. J. MODOWALL. ET AL 2,
COMBUSTION CHAMBER CROSSOVER TUBE Filed Jan. 26, 1951 lEN/TER l4 M 6 2% -};7 Z J/a Z7 CazfesJ 77Zc$3$223 (75/177 E weak/g1 (i WWM United States Patent COMBUSTION CHAMBER CROSSOVER TUBE Charles J. McDowall, New Augusta, and John B. Wheatley and Floyd G. Daugherty, Indianapolis, Ind., assignors to General Motors Corporation, Detroit, Mich a corporation of Delaware Application January 26, 1951, Serial No. 207,934
8 Claims. (Cl. 60-3937) Our invention relates to combustion apparatus, particularly to such as are used in aircraft propulsion gas turbine engines, although it may be otherwise employed.
Combustion systems for gas turbine engines are of various types. One known type, to which our invention is primarily applicable, comprises a number of ducts, com-,
monly called flame tubes or combustion liners, in which combustion is effected. These flame tubes are mounted in a combustion chamber which extends between the compressor and turbine of the engine and from which combustion air is supplied to the several flame tubes. Ordinarily, the flame tubes are disposed in a substantially parallel arrangement disposed circumferentially around the axis of the engine. Ordinarily, the combustion chamber is annular and the power output shaft of the turbine is mounted within the inner shroud of the combustion chamber.
Where a plurality of combustion chambers or flame tubes are employed, it is the usual practice to interconnect the flame tubes by tubes or sleeves commonly called crossover tubes. The principal purpose of the crossover tubes is to provide for ignition of the flame in each flame tube from the adjacent flame tube so that an ignition device is not required for each combustion space.
This invention is directed to a crossover tube and the construction of the flame tubes for reception thereoi such that the application and removal of the crossover tubes and flame tubes during assembly or servicing of the engine is greatly facilitated and such that expansion or distortion of the structure due to the high temperatures prevailing is readily accommodated. These advantages are attained by a structure of remarkable simplicity and minimum weight and cost. The principal objects of the invention are to improve combustion apparatus such as is used in gas turbine engines; to facilitate assembly and servicing of such engines; to provide an improved combustion chamber and crossover tube structure; and to provide a simple, eflicient, and inexpensive crossover tube.
The preferred manner in which these objects are achieved and the advantages of the invention will be apparent to those skilled in the art from the appended description of the preferred embodiment of the invention.
Referring to the drawing, Figure l is a transverse section of a portion of a gas turbine combustion apparatus, and Figure 2 is an enlarged sectional view taken on a plane containing the axis of a crossover tube.
The combustion apparatus is contained in a combustion chamber bounded by an outer casing or shroud 11 and an inner shroud 12, these being cylindrical. The shrouds 11 and 12 may be formed of semicylindrical sections fixed together. The shrouds define a passage for air discharged by the compressor of a gas turbine engine, which flows axially of the casing 11.
Mounted within the combustion chamber are a plurality of flame tubes or combustion liners 14. In the embodiment illustrated, there are six flame tubes, only a part of which are shown to avoid unnecessary duplication in the drawings. These flame tubes, which are generally cylindrical, are disposed with their axes parallel. They are formed with perforations to admit air for combustion from the outer chamber into the interior of the flame tubes and are fitted with fuel injection nozzles (not shown). The shrouds l1 and 12 and the flame tubes 14 are ordinarily made of heat resisting alloys such as stainless steel or inconel. The combustion products are discharged from the flame tubes into a turbine (not shown). One or preferably two of the flame tubes are provided with fuel ignition devices 16 which may be of any conventional type. Ordinarily, the ignition device is mounted on the outer shroud 11 and projects into the flame tube 14. As illustrated, the igniter is an electrical one and includes a connector 17 for a high tension circuit. Since the structure so far described is of a sort well known to those skilled in the gas turbine engine art and the details thereof are immaterial to the invention, further description is unnecessary.
When the combustion apparatus is assembled, the crossover tube is held in place by bending outwardly one or more of the tabs 31 as indicated by 31a at the top and bottom of Figure 2 to provide a locating shoulder. The reduced diameter of the central part of sleeve 24 makes it easy to pry up the tabs.
The significance of the invention may be best appreciated in connection with a consideration of the problem involved in assembly and disassembly of the engines. The flame tubes 14 must be inserted and removed individually so that it is important to have a crossover tube structure which makes it easy to assemble or disassemble them. In the assembly of the engine, before any of the tabs 31 are bent out, the crossover tube 20, as shown in Figure 2, may be inserted into the left-hand flame tube in Figure 2 until the flange 26 engages the boss of the left-hand flame tube. In this position of the crossover tube, the right-hand end of the tube is out of the way of the right hand flame tube, which may be moved into place either longitudinally of the engine or radially of the engine without interference from the crossover tube. When both flame tubes are in place, the
Patented Jan. 10, 1956 The flange 26 of crossover tube is slid to the right to the position illustrated in Figure 2 and the tab or tabs 31a are bent out completing the assembly. All of the crossover tubes are assembled in the same manner. To remove a flame tube, it it necessary only to bend inwardly the previously bent tabs so that the crossover tube can again be pushed into one flame tube so as to clear the other. Even if this releasing of the tabs should break the tabs, another pair of tabs may be used for holding the crossover tube in place when the device is reassembled.
The fit of the crossover tube in the flame tubes may be made as loose as desired. Any desired amount of looseness of the crossover tube for movement longitudinally of its own axis may be provided to accommodate expansion or distortion of the flame tubes.
It is believed that the advantages of the invention will be apparent to those skilled in the art from the foregoing. Many modifications of structure may be made within the principles of the invention, which are illustrated but not limited by the foregoing description of the preferred embodiment.
We claim:
1. A combustion apparatus comprising, in combination, means defining a chamber adapted to be supplied with air; a plurality of flame tubes in the chamber, adjacent flame tubes being provided with open opposed coaxial sockets for receiving a crossover tube to interconnect the flame tubes, the sockets being disposed to provide a gap therebetween; and a crossover tube adapted for insertion in the opposed sockets extending between the flame tubes, the crossover tube comprising a sleeve of length greater than the said gap, a shoulder thereon spaced from one end of the sleeve by a distance less than the gap, so that when the other end of the sleeve is inserted in a flame tube the sleeve clears the adjacent flame tube, and means providing an abutment against one of the flame tubes when the shoulder is lodged against the other flame tube to hold the crossover tube against displacement after assembly.
2. A combustion apparatus comprising, in combination, means defining a chamber adapted to be supplied with air; a plurality of flame tubes in the chamber, adjacent flame tubes being provided with open opposed coaxial sockets for receiving a crossover tube to interconnect the flame tubes, the sockets being disposed to provide a gap therebetween; and a crossover tube adapted for insertion in the opposed sockets extending between the flame tubes, the crossover tube comprising a sleeve of length greater than the said gap, a shoulder thereon spaced from one end of the sleeve by a distance less than the gap, so that when the other end of the sleeve is inserted in a flame tube the sleeve clears the adjacent flame tube, and means providing at least one tab on the sleeve between the shoulder and the said other end, the tab being adapted to be bent outwardly to form an abutment against one of the flame tubes when the shoulder is lodged against the other flame tube to hold the crossover tube against displacement after assembly.
3. A combustion apparatus as recited in claim 2 in which the last recited means provides a plurality of the said tabs.
4. An apparatus comprising, in combination, first and second tubes and a crossover sleeve interconnecting the tubes, the tubes being provided with opposed spaced openings and the sleeve being mounted so as to extend into the openings and extend therebetween to provide communication between the tubes, the sleeve including means providing a fixed shoulder thereon to limit the depth of inserti on thereof into the first tube and means providing at least one tab deformable outwardly from the sleeve to limit the depth of insertion thereof into the second tube, the shoulder and tab thus serving to locate and fix the sleeve in a position interconnecting the tubes.
5. An apparatus comprising, in combination, first and second tubes and a crossover sleeve interconnecting the tubes, the tubes being provided with opposed spaced openlugs and the sleeve being mounted so as to extend into the openings and extend therebetween to provide communication between the tubes, the sleeve including means providing a fixed shoulder thereon to limit the depth of insertion thereof into the first tube and means providing a plurality of tabs deformable outwardly from the sleeve to limit the depth of insertion thereof into the second tube, the shoulder and tabs thus serving to locate and fix the sleeve in a position interconnecting the tubes, the tabs being spaced from the sleeve in their original position to facilitate deformation thereof.
6. An apparatus as recited in claim 4 in which the distance of the said shoulder from one end of the sleeve is less than the distance between the said openings.
7. A crossover tube comprising a sleeve, a shoulder thereon spaced from one end of the sleeve, and means on the sleeve providing a number of tabs on the sleeve between the shoulder and the other end of the sleeve, the tabs extending away from the said other end and toward the shoulder and being adapted to be sent outwardly to form an abutment.
8. A crossover sleeve including means providing a fixed shoulder thereon and means on the sleeve providing a plurality of tabs deformable radially from the sleeve, the tabs being spaced radially from the sleeve in their original position to, facilitate deformation thereof.
References Cited in the file of this patent UNITED STATES PATENTS
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US207934A US2729938A (en) | 1951-01-26 | 1951-01-26 | Combustion chamber crossover tube |
GB1005/52A GB708862A (en) | 1951-01-26 | 1952-01-14 | Improvements in combustion apparatus |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US207934A US2729938A (en) | 1951-01-26 | 1951-01-26 | Combustion chamber crossover tube |
Publications (1)
Publication Number | Publication Date |
---|---|
US2729938A true US2729938A (en) | 1956-01-10 |
Family
ID=22772565
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US207934A Expired - Lifetime US2729938A (en) | 1951-01-26 | 1951-01-26 | Combustion chamber crossover tube |
Country Status (2)
Country | Link |
---|---|
US (1) | US2729938A (en) |
GB (1) | GB708862A (en) |
Cited By (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2832195A (en) * | 1956-04-16 | 1958-04-29 | Gen Electric | Cross-ignition tube assembly for gas turbine combustion system |
US3001366A (en) * | 1958-05-15 | 1961-09-26 | Gen Motors Corp | Combustion chamber crossover tube |
US3048015A (en) * | 1959-07-08 | 1962-08-07 | Gen Motors Corp | Combustion chamber support and igniter |
US5357745A (en) * | 1992-03-30 | 1994-10-25 | General Electric Company | Combustor cap assembly for a combustor casing of a gas turbine |
US5361577A (en) * | 1991-07-15 | 1994-11-08 | General Electric Company | Spring loaded cross-fire tube |
US5749218A (en) * | 1993-12-17 | 1998-05-12 | General Electric Co. | Wear reduction kit for gas turbine combustors |
US5896742A (en) * | 1997-03-20 | 1999-04-27 | General Electric Co. | Tapered cross-fire tube for gas turbine combustors |
US6606865B2 (en) | 2001-10-31 | 2003-08-19 | General Electric Company | Bellows type outer crossfire tube |
US20050056323A1 (en) * | 2003-09-15 | 2005-03-17 | Dennis Robb | Liquid collection basin connection assembly |
US20110197586A1 (en) * | 2010-02-15 | 2011-08-18 | General Electric Company | Systems and Methods of Providing High Pressure Air to a Head End of a Combustor |
US20120304653A1 (en) * | 2011-06-03 | 2012-12-06 | General Electric Company | Load member for transition duct in turbine system |
US20160010868A1 (en) * | 2014-06-13 | 2016-01-14 | Rolls-Royce Corporation | Combustor with spring-loaded crossover tubes |
US20160025346A1 (en) * | 2014-07-24 | 2016-01-28 | Mitsubishi Hitachi Power Systems, Ltd. | Gas turbine combustor |
US11359814B2 (en) | 2015-08-28 | 2022-06-14 | Rolls-Royce High Temperature Composites Inc. | CMC cross-over tube |
Citations (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US73221A (en) * | 1868-01-14 | Improvement in connecting the tubes with the heads of sdeface-condensees | ||
US482808A (en) * | 1892-09-20 | Stovepipe-fasten er | ||
US745618A (en) * | 1903-01-05 | 1903-12-01 | Charlie E Hubbs | Stovepipe or chimney thimble. |
US823117A (en) * | 1905-08-04 | 1906-06-12 | Oscar Grismore | Spout for sifting-machines. |
US878353A (en) * | 1907-06-24 | 1908-02-04 | Walter Allen Compton | Boiler-tube. |
US2198535A (en) * | 1940-04-23 | Pipe clamp chimney combination | ||
GB575922A (en) * | 1944-09-01 | 1946-03-11 | Lucas Ltd Joseph | Improvements relating to combustion chambers for prime movers |
US2437385A (en) * | 1941-11-21 | 1948-03-09 | Dehavilland Aircraft | Jet propulsion plant |
US2475911A (en) * | 1944-03-16 | 1949-07-12 | Power Jets Res & Dev Ltd | Combustion apparatus |
US2525207A (en) * | 1947-01-13 | 1950-10-10 | Lucas Ltd Joseph | Ignition torch for internal-combustion prime movers |
US2540642A (en) * | 1947-06-19 | 1951-02-06 | Armstrong Siddeley Motors Ltd | Multiple combustion chamber torch igniter and auxiliary fuel spray device arrangement for initiating combustion |
-
1951
- 1951-01-26 US US207934A patent/US2729938A/en not_active Expired - Lifetime
-
1952
- 1952-01-14 GB GB1005/52A patent/GB708862A/en not_active Expired
Patent Citations (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US73221A (en) * | 1868-01-14 | Improvement in connecting the tubes with the heads of sdeface-condensees | ||
US482808A (en) * | 1892-09-20 | Stovepipe-fasten er | ||
US2198535A (en) * | 1940-04-23 | Pipe clamp chimney combination | ||
US745618A (en) * | 1903-01-05 | 1903-12-01 | Charlie E Hubbs | Stovepipe or chimney thimble. |
US823117A (en) * | 1905-08-04 | 1906-06-12 | Oscar Grismore | Spout for sifting-machines. |
US878353A (en) * | 1907-06-24 | 1908-02-04 | Walter Allen Compton | Boiler-tube. |
US2437385A (en) * | 1941-11-21 | 1948-03-09 | Dehavilland Aircraft | Jet propulsion plant |
US2475911A (en) * | 1944-03-16 | 1949-07-12 | Power Jets Res & Dev Ltd | Combustion apparatus |
GB575922A (en) * | 1944-09-01 | 1946-03-11 | Lucas Ltd Joseph | Improvements relating to combustion chambers for prime movers |
US2525207A (en) * | 1947-01-13 | 1950-10-10 | Lucas Ltd Joseph | Ignition torch for internal-combustion prime movers |
US2540642A (en) * | 1947-06-19 | 1951-02-06 | Armstrong Siddeley Motors Ltd | Multiple combustion chamber torch igniter and auxiliary fuel spray device arrangement for initiating combustion |
Cited By (21)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2832195A (en) * | 1956-04-16 | 1958-04-29 | Gen Electric | Cross-ignition tube assembly for gas turbine combustion system |
US3001366A (en) * | 1958-05-15 | 1961-09-26 | Gen Motors Corp | Combustion chamber crossover tube |
US3048015A (en) * | 1959-07-08 | 1962-08-07 | Gen Motors Corp | Combustion chamber support and igniter |
US5361577A (en) * | 1991-07-15 | 1994-11-08 | General Electric Company | Spring loaded cross-fire tube |
US5357745A (en) * | 1992-03-30 | 1994-10-25 | General Electric Company | Combustor cap assembly for a combustor casing of a gas turbine |
US5749218A (en) * | 1993-12-17 | 1998-05-12 | General Electric Co. | Wear reduction kit for gas turbine combustors |
US5896742A (en) * | 1997-03-20 | 1999-04-27 | General Electric Co. | Tapered cross-fire tube for gas turbine combustors |
US6606865B2 (en) | 2001-10-31 | 2003-08-19 | General Electric Company | Bellows type outer crossfire tube |
US20060174951A1 (en) * | 2003-09-15 | 2006-08-10 | Baltimore Aircoil Company, Inc. | Liquid collection basin connection assembly |
US7059346B2 (en) * | 2003-09-15 | 2006-06-13 | Dennis Robb | Liquid collection basin connection assembly |
US20050056323A1 (en) * | 2003-09-15 | 2005-03-17 | Dennis Robb | Liquid collection basin connection assembly |
US7100634B2 (en) * | 2003-09-15 | 2006-09-05 | Baltimore Aircoil Company, Inc. | Liquid collection basin connection assembly |
US20110197586A1 (en) * | 2010-02-15 | 2011-08-18 | General Electric Company | Systems and Methods of Providing High Pressure Air to a Head End of a Combustor |
US8381526B2 (en) | 2010-02-15 | 2013-02-26 | General Electric Company | Systems and methods of providing high pressure air to a head end of a combustor |
US20120304653A1 (en) * | 2011-06-03 | 2012-12-06 | General Electric Company | Load member for transition duct in turbine system |
US8978388B2 (en) * | 2011-06-03 | 2015-03-17 | General Electric Company | Load member for transition duct in turbine system |
US20160010868A1 (en) * | 2014-06-13 | 2016-01-14 | Rolls-Royce Corporation | Combustor with spring-loaded crossover tubes |
US10161635B2 (en) * | 2014-06-13 | 2018-12-25 | Rolls-Royce Corporation | Combustor with spring-loaded crossover tubes |
US20160025346A1 (en) * | 2014-07-24 | 2016-01-28 | Mitsubishi Hitachi Power Systems, Ltd. | Gas turbine combustor |
US10401031B2 (en) * | 2014-07-24 | 2019-09-03 | Mitsubishi Hitachi Power Systems, Ltd. | Gas turbine combustor |
US11359814B2 (en) | 2015-08-28 | 2022-06-14 | Rolls-Royce High Temperature Composites Inc. | CMC cross-over tube |
Also Published As
Publication number | Publication date |
---|---|
GB708862A (en) | 1954-05-12 |
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