US20070003412A1 - Abradable material composition, a thermomechanical part or casing including a coating, and a method of fabricating or repairing a coating presenting said composition - Google Patents

Abradable material composition, a thermomechanical part or casing including a coating, and a method of fabricating or repairing a coating presenting said composition Download PDF

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Publication number
US20070003412A1
US20070003412A1 US11/476,845 US47684506A US2007003412A1 US 20070003412 A1 US20070003412 A1 US 20070003412A1 US 47684506 A US47684506 A US 47684506A US 2007003412 A1 US2007003412 A1 US 2007003412A1
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US
United States
Prior art keywords
composition
abradable
substrate
composition according
primer layer
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
US11/476,845
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English (en)
Inventor
Philippe Le Beiz
Claude Mons
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Assigned to SNECMA reassignment SNECMA ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: LE BIEZ, PHILIPPE, CHARLES, ALAIN, MONS, CLAUDE MARCEL
Publication of US20070003412A1 publication Critical patent/US20070003412A1/en
Priority to US12/464,678 priority Critical patent/US20090223632A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P6/00—Restoring or reconditioning objects
    • B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C39/00—Shaping by casting, i.e. introducing the moulding material into a mould or between confining surfaces without significant moulding pressure; Apparatus therefor
    • B29C39/02—Shaping by casting, i.e. introducing the moulding material into a mould or between confining surfaces without significant moulding pressure; Apparatus therefor for making articles of definite length, i.e. discrete articles
    • B29C39/10—Shaping by casting, i.e. introducing the moulding material into a mould or between confining surfaces without significant moulding pressure; Apparatus therefor for making articles of definite length, i.e. discrete articles incorporating preformed parts or layers, e.g. casting around inserts or for coating articles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C67/00—Shaping techniques not covered by groups B29C39/00 - B29C65/00, B29C70/00 or B29C73/00
    • B29C67/24—Shaping techniques not covered by groups B29C39/00 - B29C65/00, B29C70/00 or B29C73/00 characterised by the choice of material
    • B29C67/246—Moulding high reactive monomers or prepolymers, e.g. by reaction injection moulding [RIM], liquid injection moulding [LIM]
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
    • C08K7/00—Use of ingredients characterised by shape
    • C08K7/22—Expanded, porous or hollow particles
    • C08K7/24—Expanded, porous or hollow particles inorganic
    • C—CHEMISTRY; METALLURGY
    • C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
    • C09D—COATING COMPOSITIONS, e.g. PAINTS, VARNISHES OR LACQUERS; FILLING PASTES; CHEMICAL PAINT OR INK REMOVERS; INKS; CORRECTING FLUIDS; WOODSTAINS; PASTES OR SOLIDS FOR COLOURING OR PRINTING; USE OF MATERIALS THEREFOR
    • C09D183/00—Coating compositions based on macromolecular compounds obtained by reactions forming in the main chain of the macromolecule a linkage containing silicon, with or without sulfur, nitrogen, oxygen, or carbon only; Coating compositions based on derivatives of such polymers
    • C09D183/04—Polysiloxanes
    • 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
    • F01D11/122—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 erodable or abradable material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2083/00—Use of polymers having silicon, with or without sulfur, nitrogen, oxygen, or carbon only, in the main chain, as moulding material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/80—Repairing, retrofitting or upgrading methods
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/24—Three-dimensional ellipsoidal
    • F05D2250/241—Three-dimensional ellipsoidal spherical
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • F05D2300/437—Silicon polymers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/61—Syntactic materials, i.e. hollow spheres embedded in a matrix
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating

Definitions

  • the invention relates to an abradable material composition (or a material that can be machined by moving parts), to a thermomechanical part (such as a casing) comprising a metal substrate covered in a wear portion comprising a covering presenting such a composition, and to a turbomachine fitted with such a thermomechanical part.
  • a thermomechanical part such as a casing
  • the invention also relates to a method of fabricating or repairing an abradable covering on a metal substrate and presenting such a composition.
  • That type of abradable material is generally constituted by a matrix of hot-polymerizable resin, in particular a silicone resin, and a filler of hollow glass beads, for example.
  • Hollow glass beads are microspheres serving firstly to reduce the density of the covering composition, and secondly to contribute to the ability of the abradable material to be abraded.
  • silicone resins has replaced the earlier use of organic resins which present insufficient mechanical strength, and, on being abraded, give rise to powder that, on combustion, creates residues that deflagrate at high temperatures and under high pressures.
  • new-generation turbine engines have hollow blades in their high pressure turbines that present perforations for ventilation or cooling channels connecting an internal cooling passage to the outside of the blade via ever-smaller diameters.
  • An object of the present invention is to provide an abradable material composition for which the wear debris is capable of withstanding high temperatures, and a method of obtaining a part covered in said material whose wear debris can withstand temperatures that are higher than those that can be withstood by presently-proposed compositions.
  • a particular object of the present invention is to overcome the drawbacks of prior art abradable materials in order to avoid permanently clogging ventilation perforations or cooling channels of small size due to hollow glass beads melting.
  • the hollow beads are made of refractory material, glass being excluded, so that said beads present greater resistance to high temperatures.
  • This solution also presents the additional advantage of making it possible to use hollow beads that are less expensive than glass beads, particularly if the hollow beads are combustion residues from fossil fuel power stations or steelworks, in particular if they are constituted by blast furnace slag.
  • the refractory material comprises alumina and/or silica and/or zirconia, and the refractory material preferably belongs to the family constituted by alumino-silicate materials.
  • said refractory material presents a melting temperature greater than 700° C., preferably greater than 750° C., and more preferably greater than 900° C.
  • the present invention also provides a thermomechanical part comprising a metal substrate covered in a wear portion comprising a covering presenting the above-defined composition and a bonding primer layer comprising silicone.
  • the substrate is made of titanium, steel, aluminum, or an alloy of any one of said metals.
  • the primer layer is colored.
  • thermomechanical part is intended in particular for forming a wear portion of a sealing labyrinth, associated with wipers, in particular for a booster.
  • thermomechanical part may also form part of a compressor casing, in particular for a low pressure compressor, and in particular of the booster type, or for a fan, in which the face of the wall that faces the moving blades has an abradable covering presenting the above-defined composition.
  • the present invention also provides a turbomachine including such a casing or a thermomechanical part as defined above.
  • the present invention also provides a method of fabricating or repairing an abradable covering on a metallic substrate, wherein the following steps are performed:
  • the application step b) is performed by direct injection.
  • application step b) comprises the following substeps:
  • composition as defined above e.g. a strip, a ring, or a ring portion, . . . );
  • the adhesive comprises hot-polymerizable silicone resin.
  • a step is performed prior to step a) in which a bonding primer layer is applied to the substrate, the primer layer comprising silicone, said layer being optionally colored.
  • FIG. 1 is a fragmentary half-section view of the front portion of a turbojet, with the fan and a low pressure compressor fitted with a casing.
  • the present invention relates to abradable material compositions, in particular for abradable elements in a turbojet, the description below relates to one possible and non-limiting application of this composition in accordance with the present invention.
  • FIG. 1 is a section view showing half of the front portion 10 of a turbojet on one side of a longitudinal axis 12 constituting the axis of circular symmetry of the various elements of the turbojet, and in particular of its various moving elements.
  • FIG. 1 there can be seen more precisely, amongst the various elements disposed axially around the longitudinal axis 12 and forming the conventional structure for such a turbojet, the fan 102 and the compressor 104 that operates at low pressure.
  • the fan 102 comprises a series of blades 18 projecting radially and mounted on an annular disk 20 , the assembly being mounted to rotate about the longitudinal axis 12 of the turbojet.
  • the air flow direction determines an upstream portion (to the left in FIG. 1 ) and a downstream portion (to the right in FIG. 1 ).
  • the compressor 104 comprises a plurality of sets of rotary moving blades 22 mounted on a disk or drum 24 that is secured to the disk 20 of the fan 102 .
  • FIG. 1 there can be seen three sets of moving blades 22 mounted between five sets of stationary vanes 26 mounted on a casing 28 .
  • the structure of the casing 28 is such that it includes rings 30 of abradable material on its inside face in register with the ends of the moving blades 22 .
  • abradable material of the present invention mention can be made in particular of various circumstances in which the abradable elements are used in sealing labyrinths and are placed facing wipers.
  • these rings of abradable material present a composition based on silicone resin having hollow beads that are made of refractory material, not of glass.
  • the hollow beads can be blast furnace residues constituted by coke slag. That type of material has the particular advantage of being inexpensive and of presenting grains that are sufficiently small in size.
  • hollow alumino-silicate beads of the type sold under the trade name Sovitec T212 that product being in the form of a very fine powder that is gray in color. 90% of the beads present a size that is less than 212 micrometers ( ⁇ m). Those beads present an apparent density at 20° C. lying in the range 0.37 kilograms per cubic decimeter (kg/dm 3 ) to 0.45 kg/dm 3 .
  • That product presents the following chemical composition (in % by weight): SiO 2 55% to 70% Al 2 O 3 20% to 40% Fe 2 O 3 ⁇ 10% CaO ⁇ 4% K 2 O - NaO 2 ⁇ 8% MgO ⁇ 5%
  • hollow beads e.g. silica, alumina, zirconia, . . . .
  • a silicone resin or a mixture of silicone resins is used that presents viscosity making the resin suitable for being applied directly onto the substrate or for being applied thereto by injection.
  • the composition is thus the result of mixing together said silicone resin (a resin that is vulcanizable at high temperature), a catalyst, and the above-described hollow beads, said beads representing a percentage by weight lying in the range 10% to 25%, and preferably in the range 13% to 20% of the composition.
  • the hollow beads are preferably dried by being placed in a drying oven at 150° C. for at least one hour.
  • the abradable material on the substrate which is generally made of titanium, steel, or aluminum
  • the primer layer is applied with a brush, a spray gun, or a rag.
  • a colored primer is used, e.g. Dows Corning 1200 primer which is red in color.
  • the composition is injected under pressure directly onto those locations of the substrate in question that are covered in the primer layer.
  • said composition is initially made in the form of a pre-molded element, which element may be a strip, a ring, or a ring portion, or any other element of a shape that is suitable for matching the location of the substrate that is to be covered in abradable material. Thereafter, said pre-molded element(s) is/are stuck onto the metal substrate (preferably using an adhesive made of the same type of silicone resin), and the parts are held in place for the time required for the adhesive to set, which is achieved by raising it to high temperature.
  • a polymerization cycle is performed at a temperature and for a duration that are sufficient to obtain the desired degree of hardening.
  • the abradable coating thus formed on the metal substrate can be machined so as to have the design dimensions.
  • composition in accordance with the invention can be used for fabricating rings or elements of abradable material, and also for repairing a metal thermomechanical part forming a substrate on which said abradable element constitutes the wear portion.
  • Such repair can relate to replacing an entire wear part or merely to locally retouching a damaged position, since the resin can be applied very easily to zones of small or large extent.
  • composition like putty For localized repairs, it is possible to apply the composition like putty, using a tool such as a spatula.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • General Engineering & Computer Science (AREA)
  • Organic Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Medicinal Chemistry (AREA)
  • Polymers & Plastics (AREA)
  • Health & Medical Sciences (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Materials Engineering (AREA)
  • Wood Science & Technology (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US11/476,845 2005-06-30 2006-06-29 Abradable material composition, a thermomechanical part or casing including a coating, and a method of fabricating or repairing a coating presenting said composition Abandoned US20070003412A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US12/464,678 US20090223632A1 (en) 2005-06-30 2009-05-12 Abradable material composition, a thermomechanical part or casing including a coating, and a method of fabricating or repairing a coating presenting said composition

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0506736A FR2887890B1 (fr) 2005-06-30 2005-06-30 Composition de materiau abradable, piece thermomecanique ou carter comprenant un revetement et procede de fabrication ou de reparation d'un revetement presentant cette composition
FR0506736 2005-06-30

Related Child Applications (1)

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US12/464,678 Division US20090223632A1 (en) 2005-06-30 2009-05-12 Abradable material composition, a thermomechanical part or casing including a coating, and a method of fabricating or repairing a coating presenting said composition

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US20070003412A1 true US20070003412A1 (en) 2007-01-04

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US11/476,845 Abandoned US20070003412A1 (en) 2005-06-30 2006-06-29 Abradable material composition, a thermomechanical part or casing including a coating, and a method of fabricating or repairing a coating presenting said composition
US12/464,678 Abandoned US20090223632A1 (en) 2005-06-30 2009-05-12 Abradable material composition, a thermomechanical part or casing including a coating, and a method of fabricating or repairing a coating presenting said composition

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US12/464,678 Abandoned US20090223632A1 (en) 2005-06-30 2009-05-12 Abradable material composition, a thermomechanical part or casing including a coating, and a method of fabricating or repairing a coating presenting said composition

Country Status (5)

Country Link
US (2) US20070003412A1 (fr)
EP (1) EP1739145B1 (fr)
CA (1) CA2551337A1 (fr)
DE (1) DE602006009187D1 (fr)
FR (1) FR2887890B1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110002779A1 (en) * 2008-12-24 2011-01-06 Laurent Schuster Method for Manufacturing by Molding a Machine Structural Element Having an Abradable Surface, and Structural Element
US20150209915A1 (en) * 2011-12-28 2015-07-30 Rolls-Royce Deutschland Ltd & Co Kg Method for repairing an abradable coating of a compressor of a gas turbine
US10107111B2 (en) 2012-07-20 2018-10-23 Safran Aéro Boosters Corrosion-resistant abradable covering
EP3419821A4 (fr) * 2016-02-26 2019-09-25 Standard Aero Limited Revêtement pour revêtir un carter de compresseur
US10480330B2 (en) * 2013-01-29 2019-11-19 United Technologies Corporation Blade rub material

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Publication number Priority date Publication date Assignee Title
GB0705696D0 (en) * 2007-03-24 2007-05-02 Rolls Royce Plc A method of repairing a damaged abradable coating
FR3040446B1 (fr) * 2015-08-25 2020-02-28 Safran Aircraft Engines Piece thermomecanique annulaire pour turbomachine
CN114080311B (zh) * 2019-07-11 2024-04-12 赛峰航空器发动机 通过将填充浆料注射到纤维织构中而由复合材料制造部件的方法
FR3113474B1 (fr) * 2020-08-18 2022-10-07 Safran Helicopter Engines Piece comprenant un revetement abradable et procede de fabrication associe

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US6287372B1 (en) * 2000-03-31 2001-09-11 Themec Company Incorporated Anti-corrosive coating
US20020017361A1 (en) * 1998-05-15 2002-02-14 Walker Michael S. Method for forming a fluid seal between rotating and stationary members
US20050058541A1 (en) * 2002-10-22 2005-03-17 Snecma Moteurs Casing, a compressor, a turbine, and a combustion turbine engine including such a casing

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JP2000303022A (ja) * 1999-04-21 2000-10-31 Dow Corning Toray Silicone Co Ltd エアーバッグ用シリコーンゴム系コーティング剤組成物
FR2834751B1 (fr) * 2002-01-17 2004-09-10 Snecma Moteurs Amenagement de rotor d'une turbomachine
ATE356006T1 (de) * 2002-01-29 2007-03-15 Corus Uk Ltd Laminat und verfahren zur herstellung davon
DE60231219D1 (de) * 2002-12-03 2009-04-02 Techspace Aero Sa Innerer Mantelring eines axialen Kompressors sowie dessen Verwendung

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4112179A (en) * 1975-12-10 1978-09-05 Maccalous Joseph W Method of coating with ablative heat shield materials
US4580794A (en) * 1984-11-16 1986-04-08 Jamak, Inc. Silicon rubber gasket and material
US20020017361A1 (en) * 1998-05-15 2002-02-14 Walker Michael S. Method for forming a fluid seal between rotating and stationary members
US6287372B1 (en) * 2000-03-31 2001-09-11 Themec Company Incorporated Anti-corrosive coating
US20050058541A1 (en) * 2002-10-22 2005-03-17 Snecma Moteurs Casing, a compressor, a turbine, and a combustion turbine engine including such a casing

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110002779A1 (en) * 2008-12-24 2011-01-06 Laurent Schuster Method for Manufacturing by Molding a Machine Structural Element Having an Abradable Surface, and Structural Element
US8491258B2 (en) * 2008-12-24 2013-07-23 Techspace Aero S.A. Method for manufacturing by molding a machine structural element having an abradable surface, and structural element
US20150209915A1 (en) * 2011-12-28 2015-07-30 Rolls-Royce Deutschland Ltd & Co Kg Method for repairing an abradable coating of a compressor of a gas turbine
US9403244B2 (en) * 2011-12-28 2016-08-02 Rolls-Royce Deutschland Ltd & Co Kg Method for repairing an abradable coating of a compressor of a gas turbine
US10107111B2 (en) 2012-07-20 2018-10-23 Safran Aéro Boosters Corrosion-resistant abradable covering
US10480330B2 (en) * 2013-01-29 2019-11-19 United Technologies Corporation Blade rub material
EP3419821A4 (fr) * 2016-02-26 2019-09-25 Standard Aero Limited Revêtement pour revêtir un carter de compresseur

Also Published As

Publication number Publication date
FR2887890B1 (fr) 2007-10-12
EP1739145A1 (fr) 2007-01-03
US20090223632A1 (en) 2009-09-10
CA2551337A1 (fr) 2006-12-30
DE602006009187D1 (de) 2009-10-29
EP1739145B1 (fr) 2009-09-16
FR2887890A1 (fr) 2007-01-05

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