CA2177657A1 - Abradable composition, a method of manufacturing an abradable composition and a gas turbine engine having an abradable seal - Google Patents

Abradable composition, a method of manufacturing an abradable composition and a gas turbine engine having an abradable seal

Info

Publication number
CA2177657A1
CA2177657A1 CA002177657A CA2177657A CA2177657A1 CA 2177657 A1 CA2177657 A1 CA 2177657A1 CA 002177657 A CA002177657 A CA 002177657A CA 2177657 A CA2177657 A CA 2177657A CA 2177657 A1 CA2177657 A1 CA 2177657A1
Authority
CA
Canada
Prior art keywords
spheres
hollow
aluminosilicate
abradable
aluminium phosphate
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.)
Abandoned
Application number
CA002177657A
Other languages
French (fr)
Inventor
Stephen Mason
Michael John Lawrence Percival
Gary Brian Merrill
Paul Andrew Doleman
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of CA2177657A1 publication Critical patent/CA2177657A1/en
Abandoned legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B18/00—Layered products essentially comprising ceramics, e.g. refractory products
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B20/00—Use of materials as fillers for mortars, concrete or artificial stone according to more than one of groups C04B14/00 - C04B18/00 and characterised by shape or grain distribution; Treatment of materials according to more than one of the groups C04B14/00 - C04B18/00 specially adapted to enhance their filling properties in mortars, concrete or artificial stone; Expanding or defibrillating materials
    • C04B20/0016—Granular materials, e.g. microballoons
    • C04B20/002—Hollow or porous granular materials
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B28/00—Compositions of mortars, concrete or artificial stone, containing inorganic binders or the reaction product of an inorganic and an organic binder, e.g. polycarboxylate cements
    • C04B28/34—Compositions of mortars, concrete or artificial stone, containing inorganic binders or the reaction product of an inorganic and an organic binder, e.g. polycarboxylate cements containing cold phosphate binders
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/127—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with a deformable or crushable structure, e.g. honeycomb
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/10—Sintering only
    • B22F3/11—Making porous workpieces or articles
    • B22F3/1103—Making porous workpieces or articles with particular physical characteristics
    • B22F2003/1106—Product comprising closed porosity
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2111/00—Mortars, concrete or artificial stone or mixtures to prepare them, characterised by specific function, property or use
    • C04B2111/00241—Physical properties of the materials not provided for elsewhere in C04B2111/00
    • C04B2111/00344—Materials with friction-reduced moving parts, e.g. ceramics lubricated by impregnation with carbon
    • C04B2111/00353—Sliding parts
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2111/00—Mortars, concrete or artificial stone or mixtures to prepare them, characterised by specific function, property or use
    • C04B2111/00474—Uses not provided for elsewhere in C04B2111/00
    • C04B2111/00612—Uses not provided for elsewhere in C04B2111/00 as one or more layers of a layered structure
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/65—Aspects relating to heat treatments of ceramic bodies such as green ceramics or pre-sintered ceramics, e.g. burning, sintering or melting processes
    • C04B2235/656—Aspects relating to heat treatments of ceramic bodies such as green ceramics or pre-sintered ceramics, e.g. burning, sintering or melting processes characterised by specific heating conditions during heat treatment
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/65—Aspects relating to heat treatments of ceramic bodies such as green ceramics or pre-sintered ceramics, e.g. burning, sintering or melting processes
    • C04B2235/656—Aspects relating to heat treatments of ceramic bodies such as green ceramics or pre-sintered ceramics, e.g. burning, sintering or melting processes characterised by specific heating conditions during heat treatment
    • C04B2235/6567—Treatment time
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/65—Aspects relating to heat treatments of ceramic bodies such as green ceramics or pre-sintered ceramics, e.g. burning, sintering or melting processes
    • C04B2235/66—Specific sintering techniques, e.g. centrifugal sintering
    • C04B2235/661—Multi-step sintering
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
    • C04B2237/32—Ceramic
    • C04B2237/34—Oxidic
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
    • C04B2237/32—Ceramic
    • C04B2237/34—Oxidic
    • C04B2237/341—Silica or silicates
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
    • C04B2237/32—Ceramic
    • C04B2237/34—Oxidic
    • C04B2237/343—Alumina or aluminates
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
    • C04B2237/32—Ceramic
    • C04B2237/38—Fiber or whisker reinforced
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/25—Web or sheet containing structurally defined element or component and including a second component containing structurally defined particles
    • Y10T428/252—Glass or ceramic [i.e., fired or glazed clay, cement, etc.] [porcelain, quartz, etc.]
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/25—Web or sheet containing structurally defined element or component and including a second component containing structurally defined particles
    • Y10T428/256—Heavy metal or aluminum or compound thereof
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/25—Web or sheet containing structurally defined element or component and including a second component containing structurally defined particles
    • Y10T428/259—Silicic material
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/29—Coated or structually defined flake, particle, cell, strand, strand portion, rod, filament, macroscopic fiber or mass thereof
    • Y10T428/2982—Particulate matter [e.g., sphere, flake, etc.]

Abstract

An abradable seal (46) comprises a plurality of hollow aluminosilicate spheres spheres (48) in a matrix of aluminium phosphate (50). The matrix of aluminium phosphate (50) also has an aluminosilicate filler. The hollow aluminosilicate spheres (48) have a diameter in the range of 400 to 1800 microns, preferably a diameter in the range of 800 to 1400 microns. The weight proportion of hollow aluminosilicate spheres (48) in the abradable seal (46) is 30% to 50%. The density of the abradable seal (46) is 1.5 grammes per cubic centimetre. The hollow aluminosilicate spheres (48) in the aluminium phosphate matrix (50) have a relatively high temperature capability of approximately 1300°C maximum. This makes the abradable seal (46) better able to withstand the environment in the turbine (30) of a turbofan gas turbine engine (10).

Description

2~ 77657 AN ABR~DABLE COMPOSITION
The present invention relates to abradable seals, and is particularly concerned with abradable seaLs between rotating and static components in gas turbine englnes. In particular the abradable seals are applied to the static shroud segments spaced radially from rotor blades, for example turbine blades.
In order to improve the perfcrmance and efficiency of a gas turbine engine it has been necessary to reduce the amount of air used for cooling the turbine components.
This has lead to the replacement of air cooled metallic shroud segments with uncooled ceramic matrix composite shroud segments, for example silicon carbide fibres in an alumina matrix.
Conventional abradable seals on cooled metallic shrouds comprise metallic honeycombs. These are not suitable for use on ceramic matrix composite shroud segments. Ceramic honeycombs have been applied to ceramic matrix shroud segments to form abradable seals, but these were found to cause unacceptable wear of the nickel base turbine blades. Ceramic foams have been applied to ceramic matrix shroud segments to form abradable seals, and these did not produce significant wear on the nickel base turbine blades, however tkese did not provide a satisfactory seal and they suffer irom erosion.
The present invention seeks to provide an abradable seal suitable for a ceramic matrix composite shroud segment which overcomes the above mentioned problems.
AccQrdingly the present invention provides an abradable composltion comprising hollow aluminosilicate spheres, or hollow alumina sp~eres, in an aluminium phosphate matrix.
Preferably the hollow spheres have a diameter in the range 40;3 to 1800 microns. More preferably the hollow spheres have a diameter in the ran~e 800 to 1400 microns.
Pre erably the abradable seal includes an aluminos~ licate filler.

~ 2 ~ 77657 Preferably the weight p-oportion of hollow spheres is 30% to 50%.
Prefer2bly the abrad2- l e seal has a density of ap~ oximately 1. 5 grammes pe~ cubic centimetre.
5~he present invention also provides a method of man-afacturing an abradable composition comprising the steps of:-(a) forming a paste of 2~uminium phosphate, (b) adding hollow alum- osilicate spheres, or hollow alu~ina spheres, to the paste, (c) mixing the paste and hollow aluminosilicate spheres or hollow alumina spheres to form a ceramic s lurry, (d) moulding the ceramic slurry of hollow aluminosilicate spheres, or hollow alumina spheres, and pas_e to a required shape, (e) heat treating the moulded ceramic slurry of hollow aluminosilicate spheres, or hollow alumina spheres, and paste to form an alumini m phosphate matrix containing hollow aluminosilicate spheres, or hollow alumina spheres.
Step (a) may include ~ixing aluminosilicate powder and water with alumina powde- and phosphoric acid to form the paste. Step (a) comprises mixing 54 . 3 wt%
aluminosilicate powder, 23 . 3 wt% alumina powder and 22 . 4 wt% of 96% phosphoric acid ar.d water.
Preferably step (a) ir^ludes mixing aluminosilicate powder with mono aluminium phosphate solution. Step (a) comprises mixing 4 6 . 2 wt~ mono aluminium phosphate solation and 53.8 wt% alumincsilicate powder.
Preferably in step (b) 70 wt% of the paste is mixed with 30 wt% of the hollow al ::linosilicate spheres.
Prefer2bly step (e~ i-cludes heating treating the mou'ded mixture sequentially for lO hours at 60C, for 1 hou- at 120C, for 1. 5 ho~-s at 350C, for 2 hours at 800C, for 2 hours at 1100C and for 1 hour at 1200C.
Preferably step (d) includes moulding the mixture of holiow aluminosilicate spheres, or hollow alumina spheres, and paste on a ceramic n~atrix composite material.

~ 21 77657 Preferably the ceramic matrix composite material comprises silicon carb~ de fibres in an alumina matrix, step (e) comprises hea~ treating the moulded mixture of hollow aluminosilicate spheres, or hollow alumina spheres, and paste within the mculd to bond the alumina matrix of the ceramic matrix co~posite material to the aluminium phosphate matrix containing the aluminosilicate filler and the hollow aluminosilicate spheres, or hollow alumina spheres .
o The present inven~ion also provides a gas turbine engine having an abradable seal comprising hollow aluminosilicate spheres, or hollow alumina spheres, in an aluminium phosphate matrix.
Preferably the hollow spheres have a diameter in the range 400 to 1800 microns. More preferably the hollow spheres have a diameter in the range 800 to 1400 microns.
Preferably the abradable seal includes an aluminosilicate filler.
Preferably the weight proportion of hollow spheres is 30% to 50%.
Preferably the abradable seal has a density of approximately 1. 5 grammes per cubic centimetre .
Preferably the abradable seal is bonded to a turbine shroud .
Preferably the turbine shroud comprises a ceramic matrix composite material.
Preferably the ceramic matrix composite material comprises silicon carbide fibres in an alumina matrix.
Preferably the abradable seal is bonded to the ceramic matrix composite material by an adhesive containing mono alumini~ ~ phosphate.
The present invent~ on will be more fully described by way of example with reference to the accompanying drawings, in which:-Figure 1 is a pa~t cross-sectional view through a turbofan gas turbine engine showing a turbine shroud having an abradable seal according to the present invention .

2~ 77657 Figure 2 is an enlarged cross-sectional view through the turbine shown in f igure 1.
Figure 3 is an enlarged cross-sectional view through the abradable seal shown in figure 1 and 2.
A turbofan gas turbine engine 10, shown in figure 1, comprises a fan assembly 12 ~nd a core eIlgine 14. The fan assembly 12 is positioned upstream of the core engine 14.
The fan assembly 12 is arranged in a fan duct 16 defined in part by a fan casing 18, the fan casing has an inlet 20 at its upstream end and a nozzle 22 at its downstream end.
The fan assembly 12 is driven by the core e~gine 14.
The core engine 14 comprises in axial flow series an intermediate pressure compressor 24, a high pressure compressor 26, a combustor means 28, a turbine means 30 and a nozzle 32. A portion of the air initially compressed by the fan assembly 12 flows through the inte~[Lediate and high pressure compressors 24, 26 to the comoustor means 28, which may be an annular combustor or a can-annular combustor or other suitable combustor arrangement. Fuel is burnt in the combustor means 28 to produce hot gases which flow through the turbine means 30.
The turbine means 30 drives the fan assembly 12, intermediate pressure compressor 24 and high pressure compressor 26 via respective shafts (not shown). The air driven through the nozzle 22 by the fan assembly 12 provides the majority of the thrust. The fan casing 18 is interconnected to the core engine casing by a plurality of angularly spaced spokes 34.
The turbine means 30 comprises a plurality of stages of turbine blades 36 and a plurality of stages of turbine vanes 38 arranged axially alternately, as shown more clearly in figure 2. The turbine blades 36 are secured to one or more turbine rotors (not shown) and the turbine vanes 38 are secured to the turbine casing 40. The turbine casing 40 also has a plurality of turbine shrouds 42, each one of which is arranged circumferentially around one of the stages of turbine blades 36. Each turbine shroud 42 comprises a plurality of clrcumferentially extending segments 44. The turbine shroud segments 44 are formed from a ceramic matrix compcsite material, for example the segments 44 comprise silicon carbide reinforcing -ibres in an alumina matrix, although other 5 suitable fibres and ceramic matrix materials may be used.
The use of ceramic matrix composi~e material shroud segments 44 obviates the requirement for ~ir cooling of the shroud segments 44 and hence im~-oves the efficiency of the tur^ofan gas turbine engine 10. The turbine shrouds segIrents 44 are provided with 2n abradable seal 46 with which the tips of the turbine blades 36 cooperate to form a seal.
The abradable seal 46 comprises a plurality of hollow aluminosilicate spheres, or hollow alumina spheres, 48 in a matrix of aluminium phosphate 50, as shown in figure 3.
The matrix of aluminium phosphate 50 also has an aluminosilicate filler. The hollow aluminosilicate spheres, or alumina, spheres 48 have a diameter in the range of 400 to 1800 microns, preferably a diameter in the range of 800 to 1400 microns. The weight proportion of hollow aluminosilicate, or alumina, spheres 48 in the abradable seal 46 is 30% to 50%. The density of the abradable seal is 1. 5 grammes per CUDiC centimetre . The volume proportion of hollow aluminosilicate spheres is 50%
to 60%.
The hollow aluminosilicate, or alumina, spheres in the aluminiam phosphate matrix have a relatively high temperature capability of approximately 1300C maximum.
This makes the abradable seal 46 better able to withstand the environrQent in the turbine of a ~urbofan gas turbine engine 10. The specific size of the hollow aluminosilicate, or alumina, spheres 48 gives a good compromise between abradability and erosion resistance.
The relatively high proportion of spheres 50, 30 wt% to 50 wt% gives good abradability. The use of an aluminium phosphate matrix 50 enables the ther~al expansion of the abradable seal to be matched to that of the ceramic matrix ~ 2~ 77657 , composite shroud segments 44. The thermal expansion is matcheà by the use of aluminosilicate.
T e abradable seal material ~nay be produced by mixing alumincsilicate powder, alumina powder, phosphoric acid and wa~er to produce a paste, to which is added hollow alumincsilicate spheres, or hollow alumina spheres, and these are thoroughly mixed. In more detail 54 . 3 wt~
alumincsilicate powder, 23 . 3 wt~ alumina powder and 22. 4 wt% of 96% phosphoric acid and rater are mixed together.
Initia ly the aluminosilicate and alumina powders are mixed thoroughly. Then the phcsphoric acid is added to the mixed aluminosilicate and alumina powders together with 40 . 44% of the total dry pcwder weight of distilled water. This is mixed into a ~aste, and is allowed to stand for 72 hours before use.
ACter the paste has stood f~r the allotted time, 30%
of the total weight of hollow aluminosilicate spheres is added o the paste. The hollc-~ aluminosilicate spheres are mixed thoroughly into the p2ste, if necessary using a 2(3 small amount of distilled water to form a ceramic slurry.
T:~e abradable seal material is preferably produced by mixing aluminosilicate powder and mono aluminium phosphate solution, as supplied by Alcca International 1td, of Marmion Elouse, Copenhagen Street, Worcester WRl 2E1, 2s England, using 46.2% by mass of mono aluminium phosphate solution and 53 . 8% by mass of a_aminosilicate powder. If necessary demineralised, deionised or distilled water is added to reach a suitable viscosity. The mixture is allowed to stand for 24 hours to produce a paste.
T~-e paste is mixed wit- hollow aluminosilicate spheres using 70% by mass of the paste and 30% by mass of the hollow aluminosilicate sp~eres to form a ceramic s lurry .
The ceramic slurry of hollcw aluminosilicate spheres and paste, produced by either ~ethod mentioned above, is then moulded to the re~uired shape by placing in a mould.
Once moulded the mixture of hollow aluminosilicate spheres and paste is dried and heat tre~ted according to form the . 2177657 . ~

phosphate bonds, 10 hours at 60C, 1 hour at 120C, 1. 5 hours at 350C, 2 hours zt 800C, 2 hours at 1100C and 1 hour at 1200C.
The mixture may be moulded directly onto a ceramic composite material shroud segment or alternatively may be cast in a mould to the required shape. The mixture may be cast directly onto the cera~ic composite shroud segment if the mixture has been formed using phosphoric acid, so that a bond is formed as a result of the reaction between the phosphoric acid in the mixture and the alumina matrix of the ceramic matrix composite material. If the mixture is cast separately into the required shape, the abradable seal is subsequently glued onto the ceramic composite material shroud segment. This is applicable to the mixture produced using the phosphoric acid and to the mixture produced using the aluminium phosphate solution.
In the case of silicon carbide fibres in an alumina matrix the abradable seal is attached using a mixture of 46.2~ by masS of of mono aluminium phosphate solution and 53 . 8~ by mass of aluminosilicate powder as an adhesive. The abradable seal and ceramic composite material shroud are left at room temperature for 16 hours and then heat treated according to the following schedule, 10 hours at 60C, 1 hour at 120C, 1. 5 hours at 350C, 2 hours at 800C, 2 hours at 1100C and 1 hour at 1200C.
Although the description has referred to the abradable seal being used on the turbine shroud segments of a gas turbine engine, it is possible to use the abradable seal at other suitable positions in the gas turbine engine where an abradable seal is required. It may be possible to use the abradable seal on metallic, metal matrix composite and other material components. It may be possible to use the abradable seal in other engines or apparatus where abradable seals are required.

Claims (26)

Claims:-
1. An abradable composition comprising:
hollow aluminosilicate spheres having a diameter in the range of 400 to 1800 microns, and an aluminium phosphate matrix, the hollow aluminosilicate spheres being arranged in the aluminium phosphate matrix, the weight proportion of hollow aluminosilicate spheres being 30% to 50%.
2. An abradable composition as claimed in claim 1 wherein the hollow spheres have a diameter in the range 800 to 1400 microns.
3. An abradable composition as claimed in claim 1 wherein the abradable composition includes an aluminosilicate filler.
4. An abradable composition as claimed in claim 1 wherein the abradable composition has a density of approximately 1.5 grammes per cubic centimetre.
5. An abradable composition comprising:
hollow spheres having a diameter in the range of 800 to 1800 microns, an aluminosilicate filler, and an aluminium phosphate matrix, the hollow spheres and aluminosilicate filler being arranged in the aluminium phosphate matrix, the weight proportion of hollow spheres being 30% to 50%, the hollow spheres being selected from the group comprising hollow aluminosilicate spheres and hollow alumina spheres.
6. An abradable composition as claimed in claim 5 wherein the abradable composition has a density of approximately 1.5 grammes per cubic centimetre.
7. A method of manufacturing an abradable composition comprising the steps of:-(a) forming a paste of aluminium phosphate, (b) adding hollow aluminosilicate spheres to the paste, (c) mixing the paste and hollow aluminosilicate spheres to form a ceramic slurry, (d) moulding the ceramic slurry of hollow aluminosilicate spheres and paste to a required shape, (e) heat treating the moulded ceramic slurry of hollow aluminosilicate spheres and paste to form an aluminium phosphate matrix containing hollow aluminosilicate spheres.
8. A method as claimed in claim 7 wherein in step (b) the hollow aluminosilicate spheres have a diameter of 400 to 1800 microns.
9. A method as claimed in claim 7 wherein in step (b) 50 to 70 wt% paste is mixed with 30 to 50wt% hollow aluminosilicate spheres.
10. A method as claimed in claim 7 wherein step (a) includes mixing aluminosilicate powder and water with alumina powder and phosphoric acid to form the paste.
11. A method as claimed in claim 10 wherein step (a) comprises mixing 54.3 wt% aluminosilicate powder, 23.3 wt%
alumina powder and 22.4 wt% of 96% phosphoric acid and water .
12. A method as claimed in claim 7 wherein step (a) includes mixing aluminosilicate powder with mono aluminium phosphate solution.
13. A method as claimed in claim 12 wherein step (a) comprises mixing 46.2 wt% mono aluminium phosphate solution and 53.8 wt% aluminosilicate powder.
14. A method as claimed in claim 13 wherein in step (b) 70 wt% of the paste is mixed with 30 wt% of the hollow aluminosilicate spheres.
15. A method as claimed in claim 7 wherein step (e) includes heat treating the moulded mixture sequentially for 10 hours at 60°C, for 1 hour at 120°C, for 1.5 hours at 353°C, for 2 hours at 800°C, for 2 hours at 1100°C and for 1 hour at 1200°C.
16. A method as claimed in claim 7 wherein step (d) includes moulding the mixture of hollow aluminosilicate spheres and paste on a ceramic matrix composite material.
17. A method as claimed in claim 16 wherein the ceramic composite material comprises silicon carbide fibres in an alumina matrix, step (e) comprises heat treating the moulded mixture of hollow aluminosilicate spheres and paste within the mould to bond the alumina matrix of the ceramic matrix composite to the aluminium phosphate matrix containing the aluminosilicate filler and the hollow aluminosilicate spheres.
18. A method as claimed in claim 7 including an additional step of bonding the aluminium phosphate matrix material containing an aluminosilicate filler and hollow aluminosilicate spheres to a ceramic matrix composite material.
19. A gas turbine engine having an abradable seal, the abradable seal comprising:
hollow aluminosilicate spheres having a diameter in the range 400 to 1800 microns, and an aluminium phosphate matrix, the hollow aluminosilicate spheres being arranged in the aluminium phosphate matrix, the weight proportion of hollow aluminosilicate spheres being 30% to 50%.
20. A gas turbine engine as claimed in claim 19 wherein the hollow spheres have a diameter in the range 800 to 1400 microns.
21. A gas turbine engine as claimed in claim 19 wherein the abradable seal includes an aluminosilicate filler.
22. A gas turbine engine as claimed in claim 19 wherein the abradable seal has a density of approximately 1.5 grammes per cubic centimetre.
23. A gas turbine engine as claimed in claim 19 wherein the abradable seal is bonded to a turbine shroud.
24. A gas turbine engine as claimed in claim 23 wherein the turbine shroud comprises a ceramic matrix composite material.
A gas turbine engine as claimed in claim 24 wherein the abradable seal is bonded to the alumina matrix by an adhesive containing mono aluminium phosphate.
26. A gas turbine engine having an abradable seal, the abradable seal comprising:
hollow spheres having a diameter in the range 800 to 1800 microns, an aluminosilicate filler, and an aluminium phosphate matrix, the hollow spheres and aluminosilicate filler being arranged in the aluminium phosphate matrix, the weight proportion of hollow spheres being 30% to 50%, the hollow spheres being selected from the group comprising hollow aluminosilicate spheres and hollow alumina spheres.
CA002177657A 1995-06-29 1996-05-29 Abradable composition, a method of manufacturing an abradable composition and a gas turbine engine having an abradable seal Abandoned CA2177657A1 (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11149354B2 (en) 2019-02-20 2021-10-19 General Electric Company Dense abradable coating with brittle and abradable components

Families Citing this family (67)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB9513252D0 (en) * 1995-06-29 1995-09-06 Rolls Royce Plc An abradable composition
US6197424B1 (en) 1998-03-27 2001-03-06 Siemens Westinghouse Power Corporation Use of high temperature insulation for ceramic matrix composites in gas turbines
US6013592A (en) * 1998-03-27 2000-01-11 Siemens Westinghouse Power Corporation High temperature insulation for ceramic matrix composites
US7179524B2 (en) * 1998-03-27 2007-02-20 Siemens Power Generation, Inc. Insulated ceramic matrix composite and method of manufacturing
US6641907B1 (en) 1999-12-20 2003-11-04 Siemens Westinghouse Power Corporation High temperature erosion resistant coating and material containing compacted hollow geometric shapes
US7067181B2 (en) * 2003-08-05 2006-06-27 Siemens Power Generation, Inc. Insulating ceramic based on partially filled shapes
US6977060B1 (en) 2000-03-28 2005-12-20 Siemens Westinghouse Power Corporation Method for making a high temperature erosion resistant coating and material containing compacted hollow geometric shapes
US6733907B2 (en) * 1998-03-27 2004-05-11 Siemens Westinghouse Power Corporation Hybrid ceramic material composed of insulating and structural ceramic layers
US7563504B2 (en) * 1998-03-27 2009-07-21 Siemens Energy, Inc. Utilization of discontinuous fibers for improving properties of high temperature insulation of ceramic matrix composites
US6315519B1 (en) * 1998-09-28 2001-11-13 General Electric Company Turbine inner shroud and turbine assembly containing such inner shroud
US6089825A (en) * 1998-12-18 2000-07-18 United Technologies Corporation Abradable seal having improved properties and method of producing seal
US6165542A (en) * 1998-12-23 2000-12-26 United Technologies Corporation Method for fabricating and inspecting coatings
US6235370B1 (en) 1999-03-03 2001-05-22 Siemens Westinghouse Power Corporation High temperature erosion resistant, abradable thermal barrier composite coating
SG90198A1 (en) * 1999-12-23 2002-07-23 United Technologies Corp Composite abradable material
US6365222B1 (en) 2000-10-27 2002-04-02 Siemens Westinghouse Power Corporation Abradable coating applied with cold spray technique
US6435824B1 (en) * 2000-11-08 2002-08-20 General Electric Co. Gas turbine stationary shroud made of a ceramic foam material, and its preparation
US6846574B2 (en) 2001-05-16 2005-01-25 Siemens Westinghouse Power Corporation Honeycomb structure thermal barrier coating
US6884384B2 (en) 2001-09-27 2005-04-26 Siemens Westinghouse Power Corporation Method for making a high temperature erosion resistant material containing compacted hollow geometric shapes
GB2388161A (en) * 2002-05-02 2003-11-05 Rolls Royce Plc Gas turbine engine compressor casing
GB0226997D0 (en) * 2002-11-19 2002-12-24 Welding Inst Heat resistant product
FR2840839B1 (en) 2002-06-14 2005-01-14 Snecma Moteurs METALLIC MATERIAL WHICH MAY BE USED BY ABRASION; PIECES, CARTER; PROCESS FOR PRODUCING SAID MATERIAL
US6929852B2 (en) * 2002-08-08 2005-08-16 Siemens Westinghouse Power Corporation Protective overlayer for ceramics
US6702553B1 (en) 2002-10-03 2004-03-09 General Electric Company Abradable material for clearance control
US20040188323A1 (en) * 2003-03-24 2004-09-30 Tzatzov Konstantin K. Active coating system for reducing or eliminating coke build-up during petrochemical processes
US7311790B2 (en) * 2003-04-25 2007-12-25 Siemens Power Generation, Inc. Hybrid structure using ceramic tiles and method of manufacture
US7255929B2 (en) * 2003-12-12 2007-08-14 General Electric Company Use of spray coatings to achieve non-uniform seal clearances in turbomachinery
US7351364B2 (en) * 2004-01-29 2008-04-01 Siemens Power Generation, Inc. Method of manufacturing a hybrid structure
FR2887890B1 (en) * 2005-06-30 2007-10-12 Snecma ABRADABLE MATERIAL COMPOSITION, THERMOMECHANICAL PART OR CASING COMPRISING A COATING AND PROCESS FOR MAKING OR REPAIRING A COATING HAVING THE SAME
US7628951B1 (en) * 2005-10-21 2009-12-08 Ceramatec, Inc. Process for making ceramic insulation
US7604867B2 (en) * 2005-12-20 2009-10-20 General Electric Company Particulate corrosion resistant coating composition, coated turbine component and method for coating same
US8349111B2 (en) * 2006-08-14 2013-01-08 Ceramatec, Inc. Method for joining ceramic components
US20080061515A1 (en) * 2006-09-08 2008-03-13 Eric Durocher Rim seal for a gas turbine engine
US8017240B2 (en) * 2006-09-28 2011-09-13 United Technologies Corporation Ternary carbide and nitride thermal spray abradable seal material
US20100119777A1 (en) * 2006-11-16 2010-05-13 Siemens Power Generation, Inc. Ceramic matrix composite surfaces with open features for improved bonding to coatings
GB0703827D0 (en) 2007-02-28 2007-04-11 Rolls Royce Plc Rotor seal segment
GB2449249B (en) * 2007-05-14 2009-10-21 Rolls Royce Plc Seal assembley
US20080286459A1 (en) * 2007-05-17 2008-11-20 Pratt & Whitney Canada Corp. Method for applying abradable coating
US9447503B2 (en) 2007-05-30 2016-09-20 United Technologies Corporation Closed pore ceramic composite article
MX2010011349A (en) 2008-04-17 2011-05-23 Synchrony Inc High-speed permanent magnet motor and generator with low-loss metal rotor.
US20110168450A1 (en) * 2010-01-12 2011-07-14 Halliburton Energy Services, Inc. Drill bit bearing contact pressure reduction
US9598972B2 (en) 2010-03-30 2017-03-21 United Technologies Corporation Abradable turbine air seal
DE102010026312B4 (en) 2010-07-06 2022-10-20 Phoenix Contact Gmbh & Co. Kg Connection contact and method for producing connection contacts
CA2856537A1 (en) * 2011-11-30 2013-06-06 Halliburton Energy Services, Inc. Drill bit with seal having spheres in a matrix seal material
US9726043B2 (en) 2011-12-15 2017-08-08 General Electric Company Mounting apparatus for low-ductility turbine shroud
US20130236302A1 (en) * 2012-03-12 2013-09-12 Charles Alexander Smith In-situ gas turbine rotor blade and casing clearance control
GB201213109D0 (en) * 2012-07-24 2012-09-05 Rolls Royce Plc Seal segment
EP2951241A4 (en) * 2013-01-29 2016-08-24 United Technologies Corp Blade rub material
GB201303995D0 (en) 2013-03-06 2013-04-17 Rolls Royce Plc CMC turbine engine component
GB201305701D0 (en) * 2013-03-28 2013-05-15 Rolls Royce Plc Wall section for the working gas annulus of a gas turbine engine
GB201305702D0 (en) 2013-03-28 2013-05-15 Rolls Royce Plc Seal segment
EP2997234B1 (en) 2013-05-17 2020-05-27 General Electric Company Cmc shroud support system of a gas turbine
EP3080403B1 (en) 2013-12-12 2019-05-01 General Electric Company Cmc shroud support system
CA2951638A1 (en) 2014-06-12 2015-12-17 General Electric Company Shroud hanger assembly
WO2015191169A1 (en) 2014-06-12 2015-12-17 General Electric Company Shroud hanger assembly
CA2951431C (en) 2014-06-12 2019-03-26 General Electric Company Multi-piece shroud hanger assembly
US9874104B2 (en) 2015-02-27 2018-01-23 General Electric Company Method and system for a ceramic matrix composite shroud hanger assembly
US20160305319A1 (en) * 2015-04-17 2016-10-20 General Electric Company Variable coating porosity to influence shroud and rotor durability
US9951642B2 (en) * 2015-05-08 2018-04-24 United Technologies Corporation Intermittent grooved soft abradable material to reduce blade tip temperature
US10100656B2 (en) 2015-08-25 2018-10-16 General Electric Company Coated seal slot systems for turbomachinery and methods for forming the same
US10294962B2 (en) * 2017-06-30 2019-05-21 United Technologies Corporation Turbine engine seal for high erosion environment
US11149744B2 (en) * 2017-09-19 2021-10-19 Raytheon Technologies Corporation Turbine engine seal for high erosion environment
GB201813082D0 (en) 2018-08-10 2018-09-26 Rolls Royce Plc Efficient gas turbine engine
GB201813086D0 (en) 2018-08-10 2018-09-26 Rolls Royce Plc Efficient gas turbine engine
FR3085172B1 (en) 2018-08-22 2021-03-05 Safran Aircraft Engines ABRADABLE COATING FOR TURBOMACHINE ROTATING BLADES
GB201820224D0 (en) 2018-12-12 2019-01-23 Rolls Royce Plc Seal segment for shroud ring of a gas turbine engine
EP3683406B1 (en) * 2019-01-18 2023-11-29 Ansaldo Energia Switzerland AG Abradable hybrid material, particularly for seal elements in gas turbines, and manufacturing method thereof
DE102023002027A1 (en) 2023-05-19 2024-01-18 Mercedes-Benz Group AG Method for producing a metal-ceramic composite component and the metal-ceramic composite component

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2053765A1 (en) * 1969-11-04 1971-05-13 G Hutmacher & Co Dr Insulating material for lining chill tops
FR2157106A5 (en) * 1971-10-18 1973-06-01 Electro Refractaire
US3975165A (en) * 1973-12-26 1976-08-17 Union Carbide Corporation Graded metal-to-ceramic structure for high temperature abradable seal applications and a method of producing said
GB1448320A (en) * 1974-03-04 1976-09-02 Univ Washington Lightweight inorganic material
FR2264789A1 (en) * 1974-03-21 1975-10-17 Thomson Csf Rigid syntactic foam for electronic use - mfd from inorganic spheres and inorganic binders
DE2729077A1 (en) * 1977-06-28 1979-01-11 Bayer Ag Low density inorganic tiles - made by bonding hollow siliceous spheres with phosphate(s)
US4177308A (en) * 1978-08-10 1979-12-04 The United States Of America As Represented By The Secretary Of The Air Force Non-combustible high temperature abradable seal material
GB2056502B (en) * 1979-08-21 1983-11-02 Rolls Royce Metal coated glass particles for flame spraying
JPS5632360A (en) * 1979-08-28 1981-04-01 Asahi Chemical Ind Lightweight refractory formed body
GB2072222B (en) * 1980-03-22 1983-02-16 Rolls Royce Coating compositions containing metal and glass
GB2081246B (en) * 1980-07-25 1984-03-14 Rolls Royce Thermal barrier coating composition
FR2507729B1 (en) * 1981-06-12 1986-08-22 Snecma SEAL LIKELY TO BE USED BY ABRASION AND ITS MANUFACTURING METHOD
US4450184A (en) * 1982-02-16 1984-05-22 Metco Incorporated Hollow sphere ceramic particles for abradable coatings
US4440865A (en) * 1982-03-08 1984-04-03 Salazar Paul V Refractory compositions and method
US4639388A (en) * 1985-02-12 1987-01-27 Chromalloy American Corporation Ceramic-metal composites
US5204289A (en) * 1991-10-18 1993-04-20 Minnesota Mining And Manufacturing Company Glass-based and glass-ceramic-based composites
GB9513252D0 (en) * 1995-06-29 1995-09-06 Rolls Royce Plc An abradable composition

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11149354B2 (en) 2019-02-20 2021-10-19 General Electric Company Dense abradable coating with brittle and abradable components

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US5780146A (en) 1998-07-14
JPH0913007A (en) 1997-01-14
EP0751104A2 (en) 1997-01-02
GB9513252D0 (en) 1995-09-06
US5962076A (en) 1999-10-05
EP0751104A3 (en) 1997-03-26
EP0751104B1 (en) 2004-07-28
DE69632981T2 (en) 2004-12-16
DE69632981D1 (en) 2004-09-02

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