WO2011009433A1 - Revêtement abradable à appliquer sur un composant de turbine à gaz - Google Patents

Revêtement abradable à appliquer sur un composant de turbine à gaz Download PDF

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Publication number
WO2011009433A1
WO2011009433A1 PCT/DE2010/000810 DE2010000810W WO2011009433A1 WO 2011009433 A1 WO2011009433 A1 WO 2011009433A1 DE 2010000810 W DE2010000810 W DE 2010000810W WO 2011009433 A1 WO2011009433 A1 WO 2011009433A1
Authority
WO
WIPO (PCT)
Prior art keywords
fibers
inlet lining
sealing body
reinforcing element
reinforcing
Prior art date
Application number
PCT/DE2010/000810
Other languages
German (de)
English (en)
Inventor
André Werner
Michael Schober
Siegfried Sikorski
Original Assignee
Mtu Aero Engines Gmbh
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 Mtu Aero Engines Gmbh filed Critical Mtu Aero Engines Gmbh
Publication of WO2011009433A1 publication Critical patent/WO2011009433A1/fr

Links

Classifications

    • 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
    • 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
    • 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
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/44—Free-space packings
    • F16J15/444—Free-space packings with facing materials having honeycomb-like structure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/44—Free-space packings
    • F16J15/445—Free-space packings with means for adjusting the clearance
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/28—Three-dimensional patterned
    • F05D2250/283—Three-dimensional patterned honeycomb
    • 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
    • F05D2300/612—Foam
    • 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
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to an inlet lining of the type specified in the preamble of patent claim 1 for arrangement on a gas turbine component.
  • the invention further relates to a turbomachine, in particular an aircraft engine, specified in the preamble of claim 8 type with a housing on which an inlet facing is arranged.
  • Such an inlet lining for arrangement on a gas turbine component, in particular an aircraft engine housing or an aircraft engine housing segment, is already known, for example, from DE 10 2007 053 135 A1.
  • the inlet lining which serves as part of a sealing system to increase the performance of a gas turbine, in this case comprises an elastomeric sealing body, preferably made of silicone, for cooperation with a rotor of the gas turbine that is movable relative to the inlet lining.
  • the inlet lining is usually arranged on a housing acting as a stator of the gas turbine.
  • the rotatably disposed within the housing rotor has a plurality of blades whose radially outer and possibly armored blade tips when moving the rotor strip the inlet lining and produce by material removal depressions in this inlet lining.
  • the smallest possible radial gap between the rotor and the housing is achieved, which improves the aerodynamic properties of the gas turbine.
  • the removal of material usually does not take place over the entire circumference of the inlet lining, but usually only sickle-shaped. The aim is always to minimize the aerodynamic flow through this radial gap and thus aerodynamic gap losses from a high-pressure side of the rotor blades to a low-pressure side in order to ensure high efficiency.
  • Object of the present invention is to provide an inlet lining, which allows an improved gap attitude.
  • Another object of the invention is to provide a turbomachine with an improved gap attitude.
  • the objects are achieved by an inlet lining with the features of claim 1 for placement on a gas turbine component and by a turbomachine with the features of claim 8.
  • Advantageous embodiments with advantageous developments of the invention are specified in the dependent claims, wherein advantageous embodiments of the inlet lining are to be regarded as advantageous embodiments of the turbomachine and vice versa.
  • An inlet lining which allows an improved gap attitude, according to the invention o created by the fact that in the elastomeric sealing body at least one shape-stabilizing
  • Reinforcement element is embedded.
  • the reinforcing element prevents unnecessary damage to the elastomeric sealing body when tearing a rotor or the like on the inlet lining by tearing larger elastomer areas, cracking, overstretching beyond the nominal extent and the like.
  • the reinforcing element advantageously increases the service life of the inlet lining. Instead of a single reinforcing element, two or more reinforcing elements may be provided.
  • the reinforcing element is at least partially honeycomb-shaped and / or fiber carpet-shaped and / or weave-shaped and / or jelly-shaped and / or Multiaxialgelegeförmig and / or braided 5 and / or mat-shaped and / or felt-shaped.
  • the inlet lining can be structurally made particularly flexible in order to optimally take account of different geometries and requirement profiles. It can also be provided that the reinforcing element is uniform over the predominant and / or the entire extension region of the inlet lining.
  • the reinforcing element inorganic reinforcing fibers in particular basalt fibers and / or boron fibers and / or glass fibers and / or ceramic fibers and / or silica fibers, and / or metallic reinforcing fibers and / or organic reinforcing fibers, in particular aramid fibers and / or carbon fibers and or polyester fibers and / or nylon fibers and / or polyethylene fibers and / or polyacrylamide fibers.
  • the elastomeric sealing body can be advantageously formed as a fiber-elastomer composite part with high specific stiffness and strength and is therefore ideal for lightweight applications.
  • the respective mechanical and thermal properties of the inlet lining can be adjusted selectively over a variety of parameters such as the material combination reinforcing element-elastomer sealing body, fiber angle, fiber volume fraction, layer order and the like.
  • the reinforcing element comprising flattened reinforcing fibers
  • notch-sensitive fibers can be protected from damage during the production of the enema lining.
  • the adhesion between the reinforcing element and the elastomeric sealing body can be considerably increased by an adhesion-promoting application.
  • the reinforcing element comprises short fibers and / or long fibers and / or continuous fibers and / or a wire. In this way, the mechanical properties of the inlet lining can be optimally adapted to its respective application, with the highest stiffness and strength values are achieved with continuous fibers and / or wire.
  • the embedding of the reinforcing element in the elastomeric sealing body can be carried out, for example, directly in an extruder, depending on the configuration of the reinforcing element.
  • the elastomeric sealant acrylonitrile-butadiene-styrene and / or a polyamide and / or a polylacetate and / or a polyacrylate and / or a polycarbonate and / or a polyethylene terephthalate and / or poly- ethylene and / or polypropylene and / or polystyrene and / or a polyether ketone and / or Polyvinyl chloride and / or a polyphenylene sulfide and / or a polysulfone and / or a polyetherimide and / or polytetrafluoroethene and / or a polyurethane and / or a polyisoprene and / or a silicone.
  • the elastomeric sealing body consists of a material mixture, a multilayer material or only of a single material.
  • the inlet lining is partially made of a thermoset, another way to adapt the mechanical and thermal properties of the inlet lining is possible.
  • the reinforcing element is also embedded in a duroplastic region of the inlet lining.
  • An aircraft engine comprising a housing, on which an inlet lining is arranged, which comprises an elastomeric sealing body for cooperating with a rotor arranged movable relative to the inlet lining within the housing.
  • an improved gap attitude according to the invention is achieved in that at least one shape-stabilizing reinforcing element is embedded in the elastomeric sealing body.
  • the reinforcing element prevents unnecessary damage to the elastomeric sealing body, for example by tearing larger elastomer areas, cracking, overhanging beyond the nominal extent or the like.
  • the reinforcing element advantageously increases the service life of the inlet lining.
  • the housing and / or the inlet lining is formed segmented or are. Instead of a single reinforcing element, two or more reinforcing elements may be provided.
  • the inlet lining is designed according to one of the preceding exemplary embodiments. The resulting benefits can be found in the corresponding descriptions.
  • turbomachine being designed as a compressor, in particular as a high-pressure and / or low-pressure compressor, and / or as a turbine, in particular as a high-pressure and / or low-pressure turbine.
  • a compressor in particular as a high-pressure and / or low-pressure compressor
  • a turbine in particular as a high-pressure and / or low-pressure turbine.
  • FIG. 1 is a fragmentary schematic representation of a first exemplary embodiment o an inlet lining with a honeycomb-shaped reinforcing element.
  • FIG. 2 is a fragmentary schematic representation of a second exemplary embodiment of the inlet lining with a fiber-reinforced composite reinforcing element
  • FIG. 3 is a fragmentary schematic representation of a third exemplary embodiment of the inlet lining with a fabric-shaped reinforcing element.
  • Fig. 4 is a fragmentary schematic representation of a fourth embodiment o of the inlet lining with a felt-shaped reinforcing element.
  • 1 shows a fragmentary schematic illustration of a first exemplary embodiment of an inlet lining 10, which is arranged in an aircraft engine housing 12 of a compressor of a gas turbine (not shown).
  • the aircraft engine housing 12, which is also referred to as a Shroud serves as a carrier of the inlet lining 10 and is formed here segmented.
  • the inlet lining 10 which in turn may in principle be segmented or formed circumferentially, has an elastomeric sealing body 14 for cooperation with a rotor of the gas turbine which is arranged so as to be movable relative to the inlet lining 10.
  • a reinforcing element 16 is embedded in it, which in the present exemplary embodiment is honeycomb-shaped (so-called honeycomb structure).
  • the reinforcing element 16 consists of diamond fibers (eg Nomex®), while the elastomer sealing body 14 is made of a silicone.
  • Aramid fibers and silicone have the common advantage that they are very temperature resistant.
  • aramid fibers are characterized by very high strength, high impact strength, high elongation at break and good vibration damping, so that they are ideal for engine construction own.
  • the reinforcing element 16 prevents when rubbing the rotor, that it comes to an abrasion of the elastomeric sealing body 14 beyond the nominal amount. Furthermore, the reinforcing element 16 prevents larger material breaks or cracking occurring in the elastomeric sealing body 14. As a result, on the one hand, due to the shape stabilization of the elastomeric sealing body 14, an optimum gap position with minimum radial gap is ensured and, on the other hand, a considerable extension of the service life of the inlet lining 10 is achieved.
  • the reinforcing element 16 can basically extend over the entire inlet lining 10 or, as shown in FIG. 1, only over a partial area.
  • Fig. 2, Fig. 3 and Fig. 4 respectively show a detail of basic embodiments of further embodiments of the inlet cover 10 with differently shaped reinforcing elements 16.
  • the reinforcing element 16 is formed fiberteppichformig, while in the in Fig. 3 and Fig. 4 Ausrete- tion examples shown is formed in a web-shaped or felt-shaped.
  • different configurations of the reinforcing element 16 may also be provided depending on the location. be seen.
  • the reinforcing element 16 may also be embedded in multiple layers in the elastomeric sealing body 14.
  • the elastomeric sealing body 14 may in turn consist of different elastomers or elastomer mixtures and / or optionally be combined with an additional Duroplast stresses to accomplish an optimized adjustment of its mechanical and thermal properties.
  • the fiber angle, the fiber volume fraction, the layer sequence, etc. of the reinforcing element 16 can be varied.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Gasket Seals (AREA)

Abstract

L'invention concerne un revêtement abradable (10) à appliquer sur un composant de turbine à gaz, notamment un carter (12) d'un groupe motopropulseur (12) d'avion ou un segment de carter de groupe motopropulseur, d'une turbine à gaz, ledit revêtement abradable (10) comprenant un corps d'étanchéité élastomère (14) destiné à coopérer avec un autre composant de la turbine à gaz, notamment un rotor, disposé mobile par rapport au revêtement abradable, au moins un élément de renforcement (16) destiné à favoriser la stabilité dimensionnelle étant noyé dans le corps d'étanchéité élastomère (14). L'invention concerne également une machine à débit continu, notamment un groupe motopropulseur d'avion, comprenant un carter (12) sur lequel est appliqué un revêtement abradable (10).
PCT/DE2010/000810 2009-07-21 2010-07-10 Revêtement abradable à appliquer sur un composant de turbine à gaz WO2011009433A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009034025.4 2009-07-21
DE102009034025A DE102009034025A1 (de) 2009-07-21 2009-07-21 Einlaufbelag zur Anordnung an einem Gasturbinenbauteil

Publications (1)

Publication Number Publication Date
WO2011009433A1 true WO2011009433A1 (fr) 2011-01-27

Family

ID=43066562

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE2010/000810 WO2011009433A1 (fr) 2009-07-21 2010-07-10 Revêtement abradable à appliquer sur un composant de turbine à gaz

Country Status (2)

Country Link
DE (1) DE102009034025A1 (fr)
WO (1) WO2011009433A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2317079A3 (fr) * 2009-10-30 2013-09-25 Alstom Technology Ltd Système de revêtement abradable
WO2018233452A1 (fr) * 2017-06-21 2018-12-27 中国航发商用航空发动机有限责任公司 Pale de ventilateur pour moteur à double flux
CN113665039A (zh) * 2020-05-15 2021-11-19 中国航发商用航空发动机有限责任公司 一种风扇叶片平台及其制备方法

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3028882B1 (fr) * 2014-11-20 2021-05-28 Snecma Procede de realisation d'un revetement abradable multicouches avec structure tubulaire integree, et revetement abradable obtenu par un tel procede
DE102015210601A1 (de) * 2015-06-10 2016-12-15 Voith Patent Gmbh Laufrad für eine Pumpe oder Turbine

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US4349313A (en) * 1979-12-26 1982-09-14 United Technologies Corporation Abradable rub strip
US4639388A (en) * 1985-02-12 1987-01-27 Chromalloy American Corporation Ceramic-metal composites
EP1288443A1 (fr) * 2001-08-30 2003-03-05 United Technologies Corporation Etancéité abradable
DE69910408T2 (de) * 1999-12-21 2004-06-24 Techspace Aero S.A. Steifes Ringteil
DE102004031255A1 (de) * 2004-06-29 2006-01-19 Mtu Aero Engines Gmbh Einlaufbelag
EP1821011A1 (fr) * 2006-02-21 2007-08-22 United Technologies Corporation Matériau à frottement pour turbine
EP1843044A1 (fr) * 2006-04-03 2007-10-10 Rolls-Royce Deutschland Ltd & Co KG Compresseur axial pour une turbine à gaz
DE102007053135A1 (de) 2007-11-08 2009-05-14 Mtu Aero Engines Gmbh Gasturbinenbauteil, insbesondere Flugtriebwerksbauteil bzw. Verdichterbauteil
WO2009129787A1 (fr) * 2008-04-21 2009-10-29 Mtu Aero Engines Gmbh Système d'étanchéité
EP2196632A2 (fr) * 2008-12-10 2010-06-16 Rolls-Royce plc Dispositif d'étanchéité dans une turbine à gaz et procédé de fabrication

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DE4432685C1 (de) * 1994-09-14 1995-11-23 Mtu Muenchen Gmbh Anlaufbelaf für das Gehäuse einer Turbomaschine und Verfahren zur Herstellung
US6979172B1 (en) * 2002-01-03 2005-12-27 Saint-Gobain Ceramics & Plastics, Inc. Engine blade containment shroud using quartz fiber composite
US6969231B2 (en) * 2002-12-31 2005-11-29 General Electric Company Rotary machine sealing assembly
US8622694B2 (en) * 2006-08-31 2014-01-07 United Technologies Corporation Methods and systems for removably securing reusable parts to replaceable parts

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Publication number Priority date Publication date Assignee Title
US4349313A (en) * 1979-12-26 1982-09-14 United Technologies Corporation Abradable rub strip
US4639388A (en) * 1985-02-12 1987-01-27 Chromalloy American Corporation Ceramic-metal composites
DE69910408T2 (de) * 1999-12-21 2004-06-24 Techspace Aero S.A. Steifes Ringteil
EP1288443A1 (fr) * 2001-08-30 2003-03-05 United Technologies Corporation Etancéité abradable
DE102004031255A1 (de) * 2004-06-29 2006-01-19 Mtu Aero Engines Gmbh Einlaufbelag
EP1821011A1 (fr) * 2006-02-21 2007-08-22 United Technologies Corporation Matériau à frottement pour turbine
EP1843044A1 (fr) * 2006-04-03 2007-10-10 Rolls-Royce Deutschland Ltd & Co KG Compresseur axial pour une turbine à gaz
DE102007053135A1 (de) 2007-11-08 2009-05-14 Mtu Aero Engines Gmbh Gasturbinenbauteil, insbesondere Flugtriebwerksbauteil bzw. Verdichterbauteil
WO2009129787A1 (fr) * 2008-04-21 2009-10-29 Mtu Aero Engines Gmbh Système d'étanchéité
EP2196632A2 (fr) * 2008-12-10 2010-06-16 Rolls-Royce plc Dispositif d'étanchéité dans une turbine à gaz et procédé de fabrication

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2317079A3 (fr) * 2009-10-30 2013-09-25 Alstom Technology Ltd Système de revêtement abradable
US8821116B2 (en) 2009-10-30 2014-09-02 Alstom Technology Ltd. Abradable coating system
WO2018233452A1 (fr) * 2017-06-21 2018-12-27 中国航发商用航空发动机有限责任公司 Pale de ventilateur pour moteur à double flux
CN113665039A (zh) * 2020-05-15 2021-11-19 中国航发商用航空发动机有限责任公司 一种风扇叶片平台及其制备方法
CN113665039B (zh) * 2020-05-15 2023-08-04 中国航发商用航空发动机有限责任公司 一种风扇叶片平台及其制备方法

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