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EP4273370A3 - Turbine ring assembly for differential thermal expansion - Google Patents

Turbine ring assembly for differential thermal expansion Download PDF

Info

Publication number
EP4273370A3
EP4273370A3 EP23198187.9A EP23198187A EP4273370A3 EP 4273370 A3 EP4273370 A3 EP 4273370A3 EP 23198187 A EP23198187 A EP 23198187A EP 4273370 A3 EP4273370 A3 EP 4273370A3
Authority
EP
European Patent Office
Prior art keywords
ring
support structure
turbine
turbine ring
ring assembly
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.)
Pending
Application number
EP23198187.9A
Other languages
German (de)
French (fr)
Other versions
EP4273370A2 (en
Inventor
Clément ROUSSILLE
Gaël EVAIN
Adèle LYPRENDI
Lucien QUENNEHEN
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
Safran Aircraft Engines 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 Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP4273370A2 publication Critical patent/EP4273370A2/en
Publication of EP4273370A3 publication Critical patent/EP4273370A3/en
Pending legal-status Critical Current

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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6033—Ceramic matrix composites [CMC]

Landscapes

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

Abstract

La présente invention concerne un ensemble d'anneau de turbine comprenant une pluralité de secteurs d'anneau (1) en matériau composite à matrice céramique formant un anneau de turbine et une structure de support d'anneau (2), chaque secteur d'anneau (1) ayant une partie formant base annulaire (5) avec une face interne (6) définissant la face interne de l'anneau de turbine et une face externe (8) à partir de laquelle s'étend une partie d'accrochage (9) du secteur d'anneau à la structure de support d'anneau, la structure de support d'anneau (2) comprenant deux brides annulaires (11a ; 11b) entre lesquelles la partie d'accrochage de chaque secteur d'anneau est maintenue, les brides annulaires de la structure de support d'anneau présentant chacune au moins une portion inclinée (12a ; 12b ; 13a ; 13b) en appui sur les parties d'accrochage des secteurs d'anneau, ladite portion inclinée formant, lorsqu'observée en coupe méridienne, un angle non nul par rapport à la direction radiale (R) et à la direction axiale (A).The present invention relates to a turbine ring assembly comprising a plurality of ring sectors (1) of ceramic matrix composite material forming a turbine ring and a ring support structure (2), each ring sector (1) having an annular base portion (5) with an internal face (6) defining the internal face of the turbine ring and an external face (8) from which extends a hooking part (9 ) from the ring sector to the ring support structure, the ring support structure (2) comprising two annular flanges (11a; 11b) between which the hooking part of each ring sector is held, the annular flanges of the ring support structure each having at least one inclined portion (12a; 12b; 13a; 13b) resting on the attachment parts of the ring sectors, said inclined portion forming, when observed in meridian section, a non-zero angle with respect to the radial direction (R) and the axial direction (A).

EP23198187.9A 2015-05-22 2016-05-18 Turbine ring assembly for differential thermal expansion Pending EP4273370A3 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1554626A FR3036435B1 (en) 2015-05-22 2015-05-22 TURBINE RING ASSEMBLY
PCT/FR2016/051168 WO2016189223A1 (en) 2015-05-22 2016-05-18 Turbine ring assembly
EP16726369.8A EP3298246B1 (en) 2015-05-22 2016-05-18 Turbine shroud assembly allowing a differential thermal expansion

Related Parent Applications (2)

Application Number Title Priority Date Filing Date
EP16726369.8A Division EP3298246B1 (en) 2015-05-22 2016-05-18 Turbine shroud assembly allowing a differential thermal expansion
EP16726369.8A Division-Into EP3298246B1 (en) 2015-05-22 2016-05-18 Turbine shroud assembly allowing a differential thermal expansion

Publications (2)

Publication Number Publication Date
EP4273370A2 EP4273370A2 (en) 2023-11-08
EP4273370A3 true EP4273370A3 (en) 2024-02-14

Family

ID=53879645

Family Applications (2)

Application Number Title Priority Date Filing Date
EP16726369.8A Active EP3298246B1 (en) 2015-05-22 2016-05-18 Turbine shroud assembly allowing a differential thermal expansion
EP23198187.9A Pending EP4273370A3 (en) 2015-05-22 2016-05-18 Turbine ring assembly for differential thermal expansion

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP16726369.8A Active EP3298246B1 (en) 2015-05-22 2016-05-18 Turbine shroud assembly allowing a differential thermal expansion

Country Status (8)

Country Link
US (2) US10724401B2 (en)
EP (2) EP3298246B1 (en)
CN (2) CN111188655B (en)
BR (1) BR112017024871B1 (en)
CA (2) CA3228720A1 (en)
FR (1) FR3036435B1 (en)
RU (1) RU2741192C2 (en)
WO (1) WO2016189223A1 (en)

Families Citing this family (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3033825B1 (en) * 2015-03-16 2018-09-07 Safran Aircraft Engines TURBINE RING ASSEMBLY OF CERAMIC MATRIX COMPOSITE MATERIAL
US10100649B2 (en) * 2015-03-31 2018-10-16 Rolls-Royce North American Technologies Inc. Compliant rail hanger
FR3045715B1 (en) * 2015-12-18 2018-01-26 Safran Aircraft Engines TURBINE RING ASSEMBLY WITH COLD AND HOT HOLDING
FR3049003B1 (en) * 2016-03-21 2018-04-06 Safran Aircraft Engines TURBINE RING ASSEMBLY WITHOUT COLD MOUNTING SET
FR3055147B1 (en) 2016-08-19 2020-05-29 Safran Aircraft Engines TURBINE RING ASSEMBLY
FR3056632B1 (en) * 2016-09-27 2020-06-05 Safran Aircraft Engines TURBINE RING ASSEMBLY INCLUDING A COOLING AIR DISTRIBUTION ELEMENT
US10697314B2 (en) 2016-10-14 2020-06-30 Rolls-Royce Corporation Turbine shroud with I-beam construction
FR3058756B1 (en) 2016-11-15 2020-10-16 Safran Aircraft Engines TURBINE FOR TURBOMACHINE
FR3068071B1 (en) 2017-06-26 2019-11-08 Safran Aircraft Engines ASSEMBLY FOR THE PALLET CONNECTION BETWEEN A TURBINE HOUSING AND AN ANNULAR TURBOMACHINE ELEMENT
US10557365B2 (en) 2017-10-05 2020-02-11 Rolls-Royce Corporation Ceramic matrix composite blade track with mounting system having reaction load distribution features
US11035243B2 (en) * 2018-06-01 2021-06-15 Raytheon Technologies Corporation Seal assembly for gas turbine engines
US10934877B2 (en) * 2018-10-31 2021-03-02 Raytheon Technologies Corporation CMC laminate pocket BOAS with axial attachment scheme
US11008894B2 (en) 2018-10-31 2021-05-18 Raytheon Technologies Corporation BOAS spring clip
FR3090732B1 (en) * 2018-12-19 2021-01-08 Safran Aircraft Engines Turbine ring assembly with indexed flanges.
FR3093344B1 (en) * 2019-03-01 2021-06-04 Safran Ceram SET FOR A TURBOMACHINE TURBINE
US11761343B2 (en) * 2019-03-13 2023-09-19 Rtx Corporation BOAS carrier with dovetail attachments
US11015485B2 (en) 2019-04-17 2021-05-25 Rolls-Royce Corporation Seal ring for turbine shroud in gas turbine engine with arch-style support
US11021987B2 (en) * 2019-05-15 2021-06-01 Raytheon Technologies Corporation CMC BOAS arrangement
US11149563B2 (en) 2019-10-04 2021-10-19 Rolls-Royce Corporation Ceramic matrix composite blade track with mounting system having axial reaction load distribution features
US11174795B2 (en) * 2019-11-26 2021-11-16 Raytheon Technologies Corporation Seal assembly with secondary retention feature
US11230937B2 (en) * 2020-05-18 2022-01-25 Rolls-Royce North American Technologies Inc. Turbine shroud assembly with dovetail retention system
CN113882910B (en) * 2020-07-03 2024-07-12 中国航发商用航空发动机有限责任公司 Turbine outer ring connection assembly, gas turbine engine and connection method
FR3127981A1 (en) * 2021-10-08 2023-04-14 Safran Aircraft Engines TURBINE ANNULAR FERRULE
US11885225B1 (en) * 2023-01-25 2024-01-30 Rolls-Royce Corporation Turbine blade track with ceramic matrix composite segments having attachment flange draft angles

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3501246A (en) * 1967-12-29 1970-03-17 Westinghouse Electric Corp Axial fluid-flow machine
EP1350927A2 (en) * 2002-03-28 2003-10-08 General Electric Company Shroud segment, manufacturing method for a shroud segment, as well as shroud assembly for a turbine engine
GB2480766A (en) * 2010-05-28 2011-11-30 Gen Electric Turbine shroud
US20140271145A1 (en) * 2013-03-12 2014-09-18 Rolls-Royce Corporation Turbine blade track assembly

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2637650B1 (en) * 1988-10-06 1990-11-16 Alsthom Gec DEVICES FOR REDUCING ARROWS AND STRESSES IN TURBINE DIAPHRAGMS
US5961278A (en) * 1997-12-17 1999-10-05 Pratt & Whitney Canada Inc. Housing for turbine assembly
US6942203B2 (en) * 2003-11-04 2005-09-13 General Electric Company Spring mass damper system for turbine shrouds
FR2887601B1 (en) 2005-06-24 2007-10-05 Snecma Moteurs Sa MECHANICAL PIECE AND METHOD FOR MANUFACTURING SUCH A PART
US7771159B2 (en) * 2006-10-16 2010-08-10 General Electric Company High temperature seals and high temperature sealing systems
FR2942844B1 (en) * 2009-03-09 2014-06-27 Snecma TURBINE RING ASSEMBLY WITH AXIAL STOP
JP5646517B2 (en) 2009-03-09 2014-12-24 スネクマ Turbine ring assembly
JP5962887B2 (en) * 2012-02-02 2016-08-03 株式会社Ihi Wing connection structure and jet engine using the same
EP2801702B1 (en) * 2013-05-10 2020-05-06 Safran Aero Boosters SA Inner shroud of turbomachine with abradable seal

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3501246A (en) * 1967-12-29 1970-03-17 Westinghouse Electric Corp Axial fluid-flow machine
EP1350927A2 (en) * 2002-03-28 2003-10-08 General Electric Company Shroud segment, manufacturing method for a shroud segment, as well as shroud assembly for a turbine engine
GB2480766A (en) * 2010-05-28 2011-11-30 Gen Electric Turbine shroud
US20140271145A1 (en) * 2013-03-12 2014-09-18 Rolls-Royce Corporation Turbine blade track assembly

Also Published As

Publication number Publication date
US11118477B2 (en) 2021-09-14
FR3036435B1 (en) 2020-01-24
CN111188655A (en) 2020-05-22
EP3298246A1 (en) 2018-03-28
CN111188655B (en) 2022-06-24
BR112017024871B1 (en) 2023-03-07
CA2986661C (en) 2024-06-18
CN108138579B (en) 2020-03-06
WO2016189223A1 (en) 2016-12-01
FR3036435A1 (en) 2016-11-25
RU2017145079A (en) 2019-06-24
US20200291820A1 (en) 2020-09-17
US10724401B2 (en) 2020-07-28
US20180156068A1 (en) 2018-06-07
BR112017024871A2 (en) 2018-08-07
CN108138579A (en) 2018-06-08
CA2986661A1 (en) 2016-12-01
RU2017145079A3 (en) 2019-10-23
EP4273370A2 (en) 2023-11-08
RU2741192C2 (en) 2021-01-22
CA3228720A1 (en) 2016-12-01
EP3298246B1 (en) 2023-11-22

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