EP2861833B1 - Paroi stator de turbomachine recouverte d'un revetement abradable. - Google Patents

Paroi stator de turbomachine recouverte d'un revetement abradable. Download PDF

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Publication number
EP2861833B1
EP2861833B1 EP13730010.9A EP13730010A EP2861833B1 EP 2861833 B1 EP2861833 B1 EP 2861833B1 EP 13730010 A EP13730010 A EP 13730010A EP 2861833 B1 EP2861833 B1 EP 2861833B1
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EP
European Patent Office
Prior art keywords
structural support
turbine engine
portion according
stator portion
engine stator
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EP13730010.9A
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German (de)
English (en)
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EP2861833A1 (fr
Inventor
Philippe Charles Alain Le Biez
Nicolas CORNACCHIA
Lionel MARCIN
Pierre-Marie MONTFORT
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Safran Aircraft Engines SAS
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SNECMA SAS
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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
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips
    • 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
    • F01D11/125—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 with a reinforcing structure
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/005—Selecting particular materials
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2300/44—Resins
    • 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
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • 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
    • 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
    • F05D2300/614—Fibres or filaments
    • 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
    • F05D2300/70—Treatment or modification of materials
    • F05D2300/702—Reinforcement

Definitions

  • the invention relates to stator walls of turbomachines provided with abradable coatings, in particular for aircraft engines, such as fan retention housings or low-pressure compressor housings.
  • Such a housing may be formed of a plurality of contiguous wall sectors (but a closed or half-shell structure is also possible) which surround a set of rotating blades driven by the combustion gases.
  • the rotary blades In order to ensure a reduced clearance operation and thus ensure the performance requirements of the turbomachine in terms of consumption and efficiency, the rotary blades must come into contact with abradable coatings disposed on the housings.
  • an abradable coating is made of a resin-based material filled with a pore-forming agent of hollow microbeads type of refractory material and usually formed by molding or physical deposition, for example by thermal spraying, on the surface to be protected.
  • the main object of the present invention is thus to overcome such disadvantages by proposing a stator wall whose abradable coating can cover any type of surface, metallic or composite, without being subjected to such local detachments.
  • the abradable coating is found perfectly secured to the structural support, which avoids any localized detachment.
  • the invention is thus particularly suitable for anodized aluminum housing parts or surface preparation by sanding or blasting is prohibited.
  • said fibrous reinforcement comprises one or more juxtaposed folds of two-dimensional long fiber fabrics.
  • Said fibrous reinforcement may comprise a ply not impregnated with a 2D fabric of glass fibers or any other long fiber reinforcement or else several plies pre-impregnated at least in part at their periphery with 2D fiberglass fabrics or any other long fiber reinforcement.
  • said structural support may be based on a metal alloy and said peripheral portion is bonded to said structural support by means of an epoxy resin or else based on a composite material and said peripheral portion is co-cured with said support during the development of said structural support.
  • said microbead-loaded resin is a silicone or epoxy resin and said microbeads are hollow glass beads or refractory material.
  • said fixing of said abradable coating on said structural support comprises a deposit by thermal spraying, injection, molding or spatulation, so as to impregnate said fibrous reinforcement and said structural support.
  • the invention also relates to any turbomachine stator comprising an annular portion as mentioned above.
  • the figure 1 represents in section a part of axial turbomachine fan retention casing formed for example by the circumferential end-to-end of a plurality of sectors.
  • the housing surrounds a rotating assembly formed of a plurality of blades (not shown), the clearance between the inner surface of the housing and the blade tips being zero or virtually zero.
  • This annular portion of the stator comprises a structural support 10 provided on the inner side (with respect to the circulation of the combustion gases) successively with a fastening sub-layer 12 and a thermal protection coating 14 formed of a material abradable having porosities and wherein the tops of the blades can partially penetrate without undergoing significant wear.
  • the structural support 10 is a metal alloy, for example titanium or aluminum.
  • the thermal protective coating 14 is made of a material having porosities and having a satisfactory resistance to the temperatures usually encountered during operation. Conventionally, in order to constitute this abradable coating, use is made of materials based on silicone or epoxy resin loaded with a pore-forming agent of the hollow microbead type made of refractory material, especially glass.
  • the attachment sub-layer 12 for bonding the abradable coating to the surface of the structural support is formed by a fiberglass reinforcement or any other fiber reinforcement. long (carbon or aramid for example) which is partially fixed at its periphery on the structural support 10.
  • the fiber reinforcement consists of one or more folds juxtaposed two-dimensional long fiber fabrics.
  • this reinforcement preferably non-impregnated (dry) is advantageously bonded to its periphery (or at least on two of its lateral edges 12A, 12B) with the aid of a resin epoxide (or even a silicone resin when the abradable coating is silicone-based) on the structural support 10.
  • this reinforcement comprises several plies, these independent of each other can then be pre-impregnated beforehand. less in part at their periphery, in particular on their lateral edges, and then their maintenance is ensured by bonding these lateral edges on the structural support 10 using, for example, an epoxy resin.
  • This impregnation can be advantageously carried out manually (manual lamination) for example by roller or spray.
  • the central portion of the armature 12C left free is in turn impregnated during the physical deposition of the abradable coating, for example by thermal spraying powder using the known plasma deposition techniques when the fabric is composed of long metal fibers.
  • the abradable material may simply be injected, molded or spatulated so as to impregnate the fiber reinforcement and the surface of the structural support.
  • the figure 2 shows another embodiment of the invention more particularly adapted to a structural support 10 of conventionally formed composite material of a reinforcement of carbon fibers, glass, aramid or ceramic embedded in an epoxy resin or similar properties.
  • the fastening sub-layer 12 is not bonded at its periphery directly to the structural support 10 with the aid of an epoxy resin but preferably co-cured with the structural support during the preparation of the latter. ci, so that this armature is found directly integrated in the own fiber reinforcement 10A structuring the surface of this structural support. Of course, it is ensured that this cooking does not affect the central portion to remain free.
  • the structure of the attachment sub-layer 12 is however identical to the previous one and formed by a fiberglass reinforcement or any other long fiber reinforcement comprising a dry ply or several plies pre-impregnated with two-dimensional long fiber fabrics which will, however, be coked with and no longer glued to the structural support.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Laminated Bodies (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

    Arrière-plan de l'invention
  • L'invention concerne les parois stator de turbomachines munies de revêtements abradables, notamment pour moteurs d'aéronefs, tels que les carters de rétention de soufflante ou de compresseur basse pression.
  • Un tel carter peut être formé d'une pluralité de secteurs de paroi jointifs (mais une structure fermée ou en demi-coquille est aussi possible) qui entourent un ensemble d'aubes rotatives mues par les gaz de combustion. Afin d'assurer un fonctionnement à jeu réduit et assurer ainsi les performances demandées à la turbomachine en termes de consommation et de rendement, les aubes rotatives doivent entrer en contact avec des revêtements abradables disposés sur les carters. Typiquement, un revêtement abradable est constitué d'un matériau à base de résine chargé d'un agent porogène de type microbilles creuses en matériau réfractaire et formé habituellement par moulage ou dépôt physique, par exemple par projection thermique, sur la surface à protéger.
  • Or, selon la nature du matériau de la partie structurale, métallique ou composite, il peut être constaté des pertes d'adhérences du matériau abradable qui peuvent conduire à son décollement et entrainer alors des ingestions plus ou moins importantes du matériau la constituant par le flux secondaire de la turbomachine. Voir par exemple DE 10 2004 031255 A1 .
  • Afin de résoudre ce problème de perte d'adhérence, il est connu de procéder au sablage ou au toilage de la partie structurale préalablement au dépôt de la protection thermique. Malheureusement, cette solution ne peut être généralisée aux surfaces ayant reçues un traitement électrolytique ou électrochimique de protection ou de passivation car une telle opération aurait pour conséquence de détruire ce traitement particulier.
    • Objet et résumé de l'invention
  • La présente invention a donc pour but principal de pallier de tels inconvénients en proposant une paroi stator dont le revêtement abradable peut recouvrir tout type de surface, métallique ou composite, sans être soumis à de tels décollements locaux.
  • Ce but est atteint grâce à une partie annulaire de stator de turbomachine selon la revendication 1.
  • Ainsi, en traversant une armature fibreuse à fibres longues, le revêtement abradable se retrouve parfaitement solidarisé au support structural, ce qui évite tout décollement localisé. L'invention est ainsi particulièrement adaptée à des parties de carter en aluminium anodisé ou une préparation de surface par toilage ou sablage est interdite.
  • Selon une disposition avantageuse, ladite armature fibreuse comporte un ou plusieurs plis juxtaposés de tissus de fibres longues à deux dimensions. Ladite armature fibreuse peut comporter un pli non imprégné d'un tissu 2D de fibres de verre ou de tout autre renfort à fibres longues ou encore plusieurs plis pré-imprégnés au moins en partie à leur périphérie de tissus 2D de fibres de verre ou de tout autre renfort à fibres longues.
  • Selon une autre disposition avantageuse, ledit support structural peut être à base d'alliage métallique et ladite partie périphérique est collée au dit support structural au moyen d'une résine époxyde ou encore à base de matériau composite et ladite partie périphérique est cocuite avec ledit support structural lors de l'élaboration dudit support structural.
  • De préférence, ladite résine chargée de microbilles est une résine de silicone ou époxyde et lesdites microbilles sont des billes creuses de verre ou d'un matériau réfractaire.
  • Avantageusement, ladite fixation dudit revêtement abradable sur ledit support structural comporte un dépôt par projection thermique, injection, moulage ou encore spatulage, de façon à imprégner ladite armature fibreuse et ledit support structural.
  • L'invention concerne également tout stator de turbomachine comportant une partie annulaire telle que précitée.
    • Brève description des dessins
  • D'autres caractéristiques et avantages de la présente invention ressortiront de la description faite ci-dessous, en référence aux dessins annexés qui en illustrent un exemple de réalisation dépourvu de tout caractère limitatif et sur lesquels :
    • la figure 1 est une vue en coupe d'une partie annulaire métallique de stator de turbomachine selon l'invention ; et
    • la figure 2 est une vue en coupe d'une partie annulaire composite de stator de turbomachine selon l'invention.
    Description détaillée d'un mode de réalisation
  • La figure 1 représente en coupe une partie de carter de rétention de soufflante de turbomachine axiale formé par exemple par la mise bout à bout en direction circonférentielle d'une pluralité de secteurs. Le carter entoure un ensemble tournant formé d'une pluralité d'aubes (non représentées), le jeu entre la surface interne du carter et les sommets des aubes étant nul ou quasi-nul.
  • Cette partie annulaire de stator comprend un support structural 10 muni du côté interne (par rapport à la circulation des gaz de combustion) successivement d'une sous-couche d'accrochage 12 et d'un revêtement de protection thermique 14 formé d'un matériau abradable comportant des porosités et dans lequel les sommets des aubes peuvent partiellement pénétrer sans subir d'usure importante.
  • Dans ce premier mode de réalisation, le support structural 10 est un alliage métallique, par exemple de titane ou d'aluminium.
  • Le revêtement de protection thermique 14 est réalisé en un matériau comportant des porosités et ayant une tenue satisfaisante aux températures habituellement rencontrées en fonctionnement. Classiquement, pour constituer ce revêtement abradable, on recourt à des matériaux à base de résine de silicone ou époxyde chargés d'un agent porogène de type microbilles creuses en matériau réfractaire, verre notamment.
  • Selon l'invention, la sous-couche d'accrochage 12 permettant la liaison du revêtement abradable avec la surface du support structural est formée par une armature de fibres de verre ou tout autre renfort à fibres longues (carbone ou aramide par exemple) qui est solidarisée en partie à sa périphérie sur le support structural 10.
  • L'armature de fibres est constituée d'un ou plusieurs plis juxtaposés de tissus de fibres longues à deux dimensions. Lorsque cette armature ne comporte qu'un seul pli, celui-ci alors de préférence non imprégné (sec) est avantageusement collé à sa périphérie (ou au moins sur deux de ses bords latéraux 12A, 12B) à l'aide d'une résine époxyde (ou bien encore une résine silicone lorsque le revêtement abradable est à base de silicone) sur le support structural 10. Par contre, lorsque cette armature comporte plusieurs plis, ceux-ci indépendants les uns des autres peuvent alors être préalablement pré-imprégnés au moins en partie à leur périphérie, notamment sur leurs bords latéraux, puis leur maintien est assuré par collage de ces bords latéraux sur le support structural 10 à l'aide par exemple d'une résine époxyde. Cette imprégnation peut être avantageusement réalisée manuellement (stratification à la main) par exemple au rouleau ou au pistolet.
  • Dans ces deux configurations, la partie centrale de l'armature 12C laissée libre (c'est à dire non collée au support structural) est quant à elle imprégnée lors du dépôt physique du revêtement abradable, par exemple par projection thermique de poudre en utilisant les techniques connues de dépôt par plasma lorsque le tissu est composé de fibres longues métalliques. Dans les autres cas, le matériau abradable peut être simplement injecté, moulé ou spatulé de façon à imprégner l'armature de fibres et la surface du support structural.
  • La figure 2 montre un autre exemple de réalisation de l'invention plus particulièrement adapté à un support structural 10 en matériau composite formé classiquement d'une armature de fibres de carbone, verre, aramide ou céramique noyées dans une résine époxyde ou aux propriétés similaires. Dans ce cas, la sous-couche d'accrochage 12 n'est pas collée à sa périphérie directement sur le support structural 10 à l'aide d'une résine époxyde mais préférentiellement cocuite avec le support structural lors de l'élaboration de celui-ci, de telle sorte que cette armature se retrouve directement intégrée à la propre armature de fibres 10A structurant la surface de ce support structural. Bien entendu, on fait en sorte que cette cuisson n'affecte pas la partie centrale devant rester libre. La structure de la sous-couche d'accrochage 12 est toutefois identique à la précédente et formée par une armature de fibres de verre ou de tout autre renfort à fibres longues comportant un pli sec ou plusieurs plis pré-imprégnés de tissus de fibres longues à deux dimensions qui seront toutefois cocuits avec et non plus collés sur le support structural.

Claims (10)

  1. Partie annulaire de stator de turbomachine comportant un support structural (10) muni successivement d'une sous-couche d'accrochage (12) et d'un revêtement abradable (14) formé par une résine chargée de microbilles, caractérisée en ce que ladite sous-couche d'accrochage assurant la fixation dudit revêtement abradable sur ledit support structural est formée par une armature fibreuse à fibres longues dont seule une partie périphérique (12A, 12B) est solidarisée par collage ou cocuisson avec ledit support structural.
  2. Partie annulaire de stator de turbomachine selon la revendication 1, caractérisée en ce que ladite armature fibreuse comporte un ou plusieurs plis juxtaposés de tissus de fibres longues à deux dimensions.
  3. Partie annulaire de stator de turbomachine selon la revendication 2, caractérisée en ce que ladite armature fibreuse comporte un pli non imprégné d'un tissu 2D de fibres de verre ou de tout autre renfort à fibres longues.
  4. Partie annulaire de stator de turbomachine selon la revendication 2, caractérisée en ce que ladite armature fibreuse comporte plusieurs plis pré-imprégnés au moins en partie à leur périphérie de tissus 2D de fibres de verre ou de tout autre renfort à fibres longues.
  5. Partie annulaire de stator de turbomachine selon la revendication 1, caractérisée en ce que lorsque ledit support structural est à base d'alliage métallique, ladite partie périphérique est collée avec ledit support structural au moyen d'une résine époxyde.
  6. Partie annulaire de stator de turbomachine selon la revendication 1, caractérisée en ce que lorsque ledit support structural est à base de matériau composite, ladite partie périphérique est cocuite avec ledit support structural lors de l'élaboration dudit support structural.
  7. Partie annulaire de stator de turbomachine selon la revendication 1, caractérisée en ce que ladite résine chargée de microbilles est une résine de silicone ou époxyde.
  8. Partie annulaire de stator de turbomachine selon la revendication 7, caractérisée en ce que lesdites microbilles sont des billes creuses de verre ou d'un matériau réfractaire.
  9. Partie annulaire de stator de turbomachine selon l'une quelconque des revendications 1 à 8, caractérisée en ce que ladite fixation dudit revêtement abradable sur ledit support structural comporte un dépôt par projection thermique, injection, moulage ou encore spatulage, de façon à imprégner ladite armature fibreuse et ledit support structural.
  10. Stator de turbomachine comportant une partie annulaire selon l'une quelconque des revendications 1 à 9.
EP13730010.9A 2012-06-04 2013-05-30 Paroi stator de turbomachine recouverte d'un revetement abradable. Active EP2861833B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1255169A FR2991374B1 (fr) 2012-06-04 2012-06-04 Paroi stator de turbomachine recouverte d'un revetement abradable
PCT/FR2013/051212 WO2013182782A1 (fr) 2012-06-04 2013-05-30 Paroi stator de turbomachine recouverte d'un revetement abradable.

Publications (2)

Publication Number Publication Date
EP2861833A1 EP2861833A1 (fr) 2015-04-22
EP2861833B1 true EP2861833B1 (fr) 2016-09-28

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EP13730010.9A Active EP2861833B1 (fr) 2012-06-04 2013-05-30 Paroi stator de turbomachine recouverte d'un revetement abradable.

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US (1) US9803497B2 (fr)
EP (1) EP2861833B1 (fr)
CN (1) CN104350238B (fr)
BR (1) BR112014030181B1 (fr)
CA (1) CA2875371C (fr)
FR (1) FR2991374B1 (fr)
RU (1) RU2637302C2 (fr)
WO (1) WO2013182782A1 (fr)

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WO2017143455A1 (fr) * 2016-02-26 2017-08-31 Standard Aero Limited Revêtement pour revêtir un carter de compresseur
US10472980B2 (en) * 2017-02-14 2019-11-12 General Electric Company Gas turbine seals
US10526908B2 (en) 2017-04-25 2020-01-07 United Technologies Corporation Abradable layer with glass microballoons
KR102049051B1 (ko) * 2018-08-22 2019-11-26 엘지전자 주식회사 팬 모터 및 그 제조방법
US12084977B1 (en) 2023-10-10 2024-09-10 Rolls-Royce North American Technologies Inc. Gas turbine engine with fan track liner having triply periodic minimal surface reinforcement

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US9803497B2 (en) 2017-10-31
RU2014153637A (ru) 2016-07-27
CN104350238A (zh) 2015-02-11
CA2875371C (fr) 2019-09-03
BR112014030181A2 (pt) 2017-06-27
BR112014030181B1 (pt) 2021-10-19
CN104350238B (zh) 2016-12-07
EP2861833A1 (fr) 2015-04-22
FR2991374A1 (fr) 2013-12-06
US20150139787A1 (en) 2015-05-21
RU2637302C2 (ru) 2017-12-01
WO2013182782A1 (fr) 2013-12-12
FR2991374B1 (fr) 2016-04-08
CA2875371A1 (fr) 2013-12-12

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