US20130209261A1 - Assembly of a Blade and a Composite Carrier, Obtained by Sealing - Google Patents

Assembly of a Blade and a Composite Carrier, Obtained by Sealing Download PDF

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Publication number
US20130209261A1
US20130209261A1 US13/823,429 US201113823429A US2013209261A1 US 20130209261 A1 US20130209261 A1 US 20130209261A1 US 201113823429 A US201113823429 A US 201113823429A US 2013209261 A1 US2013209261 A1 US 2013209261A1
Authority
US
United States
Prior art keywords
assembly
recess
omc
wall
mechanical
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
US13/823,429
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English (en)
Inventor
Philippe Renard
Hervé Grelin
Sacha Berard
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 Aero Boosters SA
Original Assignee
Techspace Aero SA
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 Techspace Aero SA filed Critical Techspace Aero SA
Assigned to TECHSPACE AERO S.A. reassignment TECHSPACE AERO S.A. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: Berard, Sacha, GRELIN, HERVE, RENARD, PHILIPPE
Publication of US20130209261A1 publication Critical patent/US20130209261A1/en
Abandoned legal-status Critical Current

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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F01D9/044—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators permanently, e.g. by welding, brazing, casting or the like
    • 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
    • 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
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • 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
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/12—Light metals
    • F05D2300/121—Aluminium
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/133—Titanium
    • 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
    • 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
    • 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 present invention relates to the technical field of assemblies in the aeronautics sector, especially in turbomachine compressor rectifiers.
  • the invention relates to a (stage of a) turbomachine compressor rectifier made up of parts of an organic matrix composite and made up of at least one blading subassembly incorporating a mechanical assembly achieved by sealing.
  • “sealing” refers to the operation of fastening a part in a carrier by means of a polymer element, which may include filler or not, by mechanical locking and/or physicochemical interaction with the carrier and/or the part to be attached.
  • turbomachine compressor rectifiers made of composite material, but rather only made of a metal material, for example titanium (TA6V), steel or aluminum.
  • the blades generally have a single material and profile on a same stage, possibly with small variation in the calibration angle for aerodynamic reasons on the last stage.
  • an outer shroud serving as a casing that performs most of the mechanical functions, on blades attached to a first end on those outer shrouds by various assembly technologies (welding, riveting, bolting), and on relatively flexible inner shrouds attached to the blades at a second end but that do not perform any structural function.
  • the invention proposes a solution for assembling parts of various natures: either “metal/composite” or even “composite/composite” hybrids, while using the smallest possible quantity of metal attachment means, the latter creating many issues (mass, differential expansion, etc.).
  • Document EP 1 493 901 discloses an assembly between blades and the inner shroud of a compressor rectifier of an aeronautic engine. Each blade passes through an opening formed in the inner shroud and is attached thereto using sealing cement containing an organic polymer adhesive.
  • Document EP 1 081 335 discloses a stator assembly for a rotary machine and, more specifically, the assembly of stator blades to inner shroud abradables.
  • the stator assembly comprises a thermoplastic shoulder provided with an opening designed to receive the foot of the stator blade, and the elastomer abradable connected to the shoulder using adhesives.
  • Document DE 10 2009 010 613 discloses a method for producing a closed strip around the blades of a turbine.
  • a strip of fibrous material is inserted into a housing arranged at the free end of the blades, and a matrix is infiltrated in the fibrous material of the strip and polymerized to form a composite.
  • Document FR 1 431 558 discloses a blade structure comprising a case and two concentric enclosures, an outer enclosure and an inner closure, the latter being offset from the outer enclosure by separating means.
  • the blades are mounted gripped in holes formed facing each other in both enclosures.
  • the blades may be welded, glued or fastened on the outer enclosure, which is mounted gripped in an outer case.
  • all these parts of the blade structure may be made of synthetic resin and glued to one another.
  • the blades may also be made of metal and welded on the outer case.
  • the present invention aims to overcome the drawbacks of the state of the art.
  • the invention aims to allow the production of bladed rectifiers with a light weight and at a low cost for all compressors whose rotor is made up of discs, of a drum, or of other elements.
  • the invention also aims to allow the easy assembly of rectifier blades with varied properties, so as to best optimize the mechanical strength as well as the costs.
  • the invention also aims to allow the rectifier to be easily assembled and disassembled, thereby favoring the in-use maintenance aspects while limiting the number of metal fastening elements.
  • the invention also aims to save time during the assembly of the compressor.
  • the invention lastly aims to allow permanent and non-deformable connection of the metal or OMC (organic matrix composite) composite parts to parts made of OMC composite.
  • the mechanical assembly comprises at least one or a suitable combination of the following features:
  • a second object of the present invention relates to a rectifier stage for a turbomachine compressor comprising a mechanical assembly of a plurality of blades to a housing with an OMC wall imparting structural rigidity to the assembly, according to the above principle, the blades each comprising a foot, said recess with an OMC wall and said sealing composite cooperating to seal the feet of the blades in the recess.
  • the rectifier stage comprises at least one or a suitable combination of the following features:
  • a third object of the invention relates to a turbomachine compressor comprising one or more rectifier stages as described above.
  • FIG. 1 shows a perspective view of an assembly as in the invention and the related parts.
  • FIG. 2 diagrammatically shows the composite assembly of the invention, by thermoforming followed by overinjection, in a side view and a front view, respectively.
  • the assembly as in a preferred embodiment of the present invention is essentially made up of a subassembly 1 obtained by the sealing of a mechanical type between:
  • the composite carrier with heat-sealable or thermoplastic matrix 2 may be manufactured by any type of method allowing to obtain sufficient mechanical properties, such as for example: compression molding, injection of a thermoplastic or heat-sealable matrix, for example RTM (resin transfer molding), thermoforming or co-consolidation, etc.
  • RTM resin transfer molding
  • the invention is not limited to the use of a profiled part 2 , for example in the shape of a “U”.
  • a planar carrier may also be considered.
  • the sealing fastening composite or sealing composite or sealing material 4 has a base of a heat-sealable or thermoplastic matrix with between 0 and 70% of fibers, for example or preferably short fibers, and may be implemented by a method for injecting a thermoplastic or heat-sealable matrix or by compression molding. More generally, the filler may be any suitable mineral or organic filler. Thus, the matrix may nevertheless have a filler (with fibers) or not have a filler (pure matrix, 0% fibers).
  • the particular geometry of the foot of the blade 3 A ensures that it is positioned and maintained in the structure ( FIG. 2 ).
  • the blades 3 being sealed, the blade foot 3 A is then embedded by the fastening composite 4 mentioned above, which for example fills the profiled part 2 and thereby ensures that the blade 3 is maintained.
  • the sealing or assembly technique used as in a preferred embodiment of the invention for metal blades 3 is illustrated more particularly and very diagrammatically in FIG. 2 .
  • the structural part or carrier structure 2 is provided by a U-shaped profile part 2 made of a thermoplastic composite with long fibers obtained by thermoforming (the opening of the “U” is oriented toward the outside relative to the blade).
  • Thermoplastic resin with a short fiber filler 4 is injected to fill the hollow volume that remains once the foot of the blade 3 A is positioned in the carrier structure 2 .
  • material is over-injected at the level of the areas that do not allow to obtain the geometry by thermoforming (not shown). Filling with the sealing material to produce the mechanical and/or physicochemical connection is for example achieved in a second step or, if possible, at the same time as the composite structural part is produced.
  • the material of the U-shaped composite carrier 2 and the sealing material 4 are identical or chemically compatible (for example, thermoplastic materials of the same nature), so as to produce chemical attachment between them.
  • the resulting “material” connection ultimately amounts in only producing a single homogenous part, which is an additional advantage in terms of mechanical strength of the assembly.
  • the subassembly 1 belonging to the rectifier stage is in the shape of a ring or of a sector fastened to an outer shroud or to a case by means of mechanical fasteners, such as lock bolts (not shown).

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Composite Materials (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US13/823,429 2010-09-16 2011-09-07 Assembly of a Blade and a Composite Carrier, Obtained by Sealing Abandoned US20130209261A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP10009660.1A EP2431571B1 (fr) 2010-09-16 2010-09-16 Assemblage d'un aube et d'un support composite par scellage
EP10009660.1 2010-09-16
PCT/EP2011/065445 WO2012034906A1 (fr) 2010-09-16 2011-09-07 Assemblage d'une aube et d'un support composite par scellage

Publications (1)

Publication Number Publication Date
US20130209261A1 true US20130209261A1 (en) 2013-08-15

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US13/823,429 Abandoned US20130209261A1 (en) 2010-09-16 2011-09-07 Assembly of a Blade and a Composite Carrier, Obtained by Sealing

Country Status (6)

Country Link
US (1) US20130209261A1 (zh)
EP (1) EP2431571B1 (zh)
CN (1) CN103168149B (zh)
CA (1) CA2811069C (zh)
RU (1) RU2583183C2 (zh)
WO (1) WO2012034906A1 (zh)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160047257A1 (en) * 2014-08-18 2016-02-18 Rolls-Royce Plc Mounting arrangement for aerofoil body
US20170335699A1 (en) * 2016-05-19 2017-11-23 Honeywell International Inc. Inter-turbine ducts
US11143402B2 (en) 2017-01-27 2021-10-12 General Electric Company Unitary flow path structure
US11149569B2 (en) * 2017-02-23 2021-10-19 General Electric Company Flow path assembly with airfoils inserted through flow path boundary
US11149575B2 (en) 2017-02-07 2021-10-19 General Electric Company Airfoil fluid curtain to mitigate or prevent flow path leakage
US11286799B2 (en) 2017-02-23 2022-03-29 General Electric Company Methods and assemblies for attaching airfoils within a flow path
US11384651B2 (en) 2017-02-23 2022-07-12 General Electric Company Methods and features for positioning a flow path inner boundary within a flow path assembly
US11391171B2 (en) 2017-02-23 2022-07-19 General Electric Company Methods and features for positioning a flow path assembly within a gas turbine engine
US11739663B2 (en) 2017-06-12 2023-08-29 General Electric Company CTE matching hanger support for CMC structures

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3026674B1 (fr) * 2014-10-07 2017-03-31 Snecma Procede de demoulage d'un materiau composite a matrice organique
BE1026884B1 (fr) * 2018-12-18 2020-07-22 Safran Aero Boosters Sa Etage statorique d’un compresseur d’une turbomachine d’aéronef
CN111734499B (zh) * 2020-04-21 2022-08-19 中国航发沈阳发动机研究所 一种增压级静子叶片限位块及具有其的增压级静子部件
CN111636926B (zh) * 2020-06-16 2022-01-18 南京航空航天大学 陶瓷基复合材料t形涡轮转子结构

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Publication number Priority date Publication date Assignee Title
US4832568A (en) * 1982-02-26 1989-05-23 General Electric Company Turbomachine airfoil mounting assembly
US5074749A (en) * 1989-05-23 1991-12-24 Societe Europeenne De Propulsion Turbine stator for a turbojet, and method of manufacture
US6196794B1 (en) * 1998-04-08 2001-03-06 Honda Giken Kogyo Kabushiki Kaisha Gas turbine stator vane structure and unit for constituting same
US6543995B1 (en) * 1999-08-09 2003-04-08 United Technologies Corporation Stator vane and stator assembly for a rotary machine
US8182213B2 (en) * 2009-04-22 2012-05-22 Pratt & Whitney Canada Corp. Vane assembly with removable vanes

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FR1431558A (fr) 1964-05-07 1966-03-11 Rolls Royce Structure à ailettes
SU1479705A1 (ru) * 1986-12-02 1989-05-15 В.Н.Меньшаков и М.В.Светухин Рабочее колесо центробежного насоса
FR2654463A1 (fr) * 1989-11-15 1991-05-17 Snecma Element de stator de turbomachine.
US6425736B1 (en) * 1999-08-09 2002-07-30 United Technologies Corporation Stator assembly for a rotary machine and method for making the stator assembly
FR2856749B1 (fr) * 2003-06-30 2005-09-23 Snecma Moteurs Redresseur de compresseur de moteur aeronautique a aubes collees
US8348604B2 (en) * 2008-03-17 2013-01-08 Rolls-Royce Corporation Airfoil assembly and method of forming same
DE102009010613A1 (de) * 2009-02-25 2010-09-02 Siemens Aktiengesellschaft Verfahren zum Anbringen bzw. Herstellen eines geschlossenen Deckbandes für eine Laufbeschaufelung einer Turbinenstufe sowie Laufbeschaufelung einer Turbinenstufe für eine Turbine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4832568A (en) * 1982-02-26 1989-05-23 General Electric Company Turbomachine airfoil mounting assembly
US5074749A (en) * 1989-05-23 1991-12-24 Societe Europeenne De Propulsion Turbine stator for a turbojet, and method of manufacture
US6196794B1 (en) * 1998-04-08 2001-03-06 Honda Giken Kogyo Kabushiki Kaisha Gas turbine stator vane structure and unit for constituting same
US6543995B1 (en) * 1999-08-09 2003-04-08 United Technologies Corporation Stator vane and stator assembly for a rotary machine
US8182213B2 (en) * 2009-04-22 2012-05-22 Pratt & Whitney Canada Corp. Vane assembly with removable vanes

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160047257A1 (en) * 2014-08-18 2016-02-18 Rolls-Royce Plc Mounting arrangement for aerofoil body
US20170335699A1 (en) * 2016-05-19 2017-11-23 Honeywell International Inc. Inter-turbine ducts
US10294807B2 (en) * 2016-05-19 2019-05-21 Honeywell International Inc. Inter-turbine ducts
US11143402B2 (en) 2017-01-27 2021-10-12 General Electric Company Unitary flow path structure
US11149575B2 (en) 2017-02-07 2021-10-19 General Electric Company Airfoil fluid curtain to mitigate or prevent flow path leakage
US11149569B2 (en) * 2017-02-23 2021-10-19 General Electric Company Flow path assembly with airfoils inserted through flow path boundary
US11286799B2 (en) 2017-02-23 2022-03-29 General Electric Company Methods and assemblies for attaching airfoils within a flow path
US11384651B2 (en) 2017-02-23 2022-07-12 General Electric Company Methods and features for positioning a flow path inner boundary within a flow path assembly
US11391171B2 (en) 2017-02-23 2022-07-19 General Electric Company Methods and features for positioning a flow path assembly within a gas turbine engine
US11828199B2 (en) 2017-02-23 2023-11-28 General Electric Company Methods and assemblies for attaching airfoils within a flow path
US11739663B2 (en) 2017-06-12 2023-08-29 General Electric Company CTE matching hanger support for CMC structures

Also Published As

Publication number Publication date
RU2583183C2 (ru) 2016-05-10
RU2013115872A (ru) 2014-10-27
WO2012034906A1 (fr) 2012-03-22
CA2811069A1 (en) 2012-03-22
CN103168149B (zh) 2014-12-03
CA2811069C (en) 2018-04-24
CN103168149A (zh) 2013-06-19
EP2431571A1 (fr) 2012-03-21
EP2431571B1 (fr) 2013-06-05

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Legal Events

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AS Assignment

Owner name: TECHSPACE AERO S.A., BELGIUM

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:RENARD, PHILIPPE;GRELIN, HERVE;BERARD, SACHA;REEL/FRAME:030244/0317

Effective date: 20130327

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION