WO2017103411A3 - Ensemble d'anneau de turbine avec maintien élastique a froid - Google Patents

Ensemble d'anneau de turbine avec maintien élastique a froid Download PDF

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Publication number
WO2017103411A3
WO2017103411A3 PCT/FR2016/053343 FR2016053343W WO2017103411A3 WO 2017103411 A3 WO2017103411 A3 WO 2017103411A3 FR 2016053343 W FR2016053343 W FR 2016053343W WO 2017103411 A3 WO2017103411 A3 WO 2017103411A3
Authority
WO
WIPO (PCT)
Prior art keywords
ring
tab
retaining element
annular
cold
Prior art date
Application number
PCT/FR2016/053343
Other languages
English (en)
Other versions
WO2017103411A2 (fr
Inventor
Thierry TESSON
Maxime Carlin
Jordan CARON
Original Assignee
Safran Ceramics
Safran Aircraft Engines
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 Ceramics, Safran Aircraft Engines filed Critical Safran Ceramics
Priority to CN201680080640.5A priority Critical patent/CN109072705B/zh
Priority to US16/063,019 priority patent/US10378385B2/en
Priority to EP16825829.1A priority patent/EP3390782B1/fr
Publication of WO2017103411A2 publication Critical patent/WO2017103411A2/fr
Publication of WO2017103411A3 publication Critical patent/WO2017103411A3/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
    • 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
    • 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
    • F01D25/005—Selecting particular materials
    • 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
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • 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
    • F05D2250/70—Shape
    • F05D2250/75—Shape given by its similarity to a letter, e.g. T-shaped
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • 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
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/502—Thermal properties
    • F05D2300/5021—Expansivity
    • F05D2300/50212—Expansivity dissimilar
    • 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)

Abstract

Un ensemble d'anneau de turbine comprend une pluralité de secteurs d'anneau (10) en matériau composite à matrice céramique formant un anneau de turbine (1) et une structure de support d'anneau (3) comportant une première et une deuxième brides annulaires (32, 36), chaque secteur d'anneau ayant des pattes (14, 16). La première patte (14) de chaque secteur d'anneau (10) comporte une rainure annulaire (140) dans laquelle est logée une saillie annulaire (34) de la première bride (32), un jeu (J1) étant présent à froid entre la saillie annulaire (34) et la rainure annulaire (140). La deuxième patte (16) de chaque secteur d'anneau (10) est reliée à la structure de support d'anneau (3) par un élément de maintien élastique (50). la deuxième patte (16) de chaque secteur d'anneau (10) comporte au moins une ouverture (17) dans laquelle est logée une partie d'un élément de maintien (40) solidaire de la deuxième bride annulaire (36) de la structure de support d'anneau (3), un jeu (J2) étant présent à froid entre l'ouverture (17) de la deuxième patte (16) et la partie de l'élément de maintien (40) présente dans ladite ouverture, ledit élément de maintien étant en un matériau ayant un coefficient de dilatation thermique supérieur au coefficient de dilatation thermique du matériau composite à matrice céramique des secteurs d'anneau.
PCT/FR2016/053343 2015-12-18 2016-12-12 Ensemble d'anneau de turbine avec maintien élastique a froid. WO2017103411A2 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
CN201680080640.5A CN109072705B (zh) 2015-12-18 2016-12-12 在冷态下弹性保持的涡轮环组件
US16/063,019 US10378385B2 (en) 2015-12-18 2016-12-12 Turbine ring assembly with resilient retention when cold
EP16825829.1A EP3390782B1 (fr) 2015-12-18 2016-12-12 Ensemble d'anneau de turbine avec maintien élastique a froid.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1562745A FR3045716B1 (fr) 2015-12-18 2015-12-18 Ensemble d'anneau de turbine avec maintien elastique a froid
FR1562745 2015-12-18

Publications (2)

Publication Number Publication Date
WO2017103411A2 WO2017103411A2 (fr) 2017-06-22
WO2017103411A3 true WO2017103411A3 (fr) 2017-08-10

Family

ID=55451372

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/FR2016/053343 WO2017103411A2 (fr) 2015-12-18 2016-12-12 Ensemble d'anneau de turbine avec maintien élastique a froid.

Country Status (5)

Country Link
US (1) US10378385B2 (fr)
EP (1) EP3390782B1 (fr)
CN (1) CN109072705B (fr)
FR (1) FR3045716B1 (fr)
WO (1) WO2017103411A2 (fr)

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FR3033825B1 (fr) * 2015-03-16 2018-09-07 Safran Aircraft Engines Ensemble d'anneau de turbine en materiau composite a matrice ceramique
FR3049003B1 (fr) * 2016-03-21 2018-04-06 Safran Aircraft Engines Ensemble d'anneau de turbine sans jeu de montage a froid
FR3056636B1 (fr) * 2016-09-27 2020-06-05 Safran Aircraft Engines Ensemble d'anneau de turbine sans jeu de montage a froid
FR3065481B1 (fr) * 2017-04-19 2020-07-17 Safran Aircraft Engines Ensemble pour turbine, notamment pour une turbomachine
FR3068072B1 (fr) * 2017-06-26 2020-09-04 Safran Aircraft Engines Ensemble pour la liaison souple entre un carter de turbine et un element annulaire de turbomachine
US10753220B2 (en) * 2018-06-27 2020-08-25 Raytheon Technologies Corporation Gas turbine engine component
US11022002B2 (en) * 2018-06-27 2021-06-01 Raytheon Technologies Corporation Attachment body for blade outer air seal
US10815816B2 (en) * 2018-09-24 2020-10-27 General Electric Company Containment case active clearance control structure
FR3090732B1 (fr) * 2018-12-19 2021-01-08 Safran Aircraft Engines Ensemble d’anneau de turbine avec flasques indexés.
US11174795B2 (en) 2019-11-26 2021-11-16 Raytheon Technologies Corporation Seal assembly with secondary retention feature
IT201900023850A1 (it) * 2019-12-12 2021-06-12 Nuovo Pignone Tecnologie Srl Struttura di tenuta composita per una macchina, e metodo per produrre la struttura di tenuta composita
US11066947B2 (en) 2019-12-18 2021-07-20 Rolls-Royce Corporation Turbine shroud assembly with sealed pin mounting arrangement
US11143050B2 (en) 2020-02-13 2021-10-12 Raytheon Technologies Corporation Seal assembly with reduced pressure load arrangement
US11215064B2 (en) * 2020-03-13 2022-01-04 Raytheon Technologies Corporation Compact pin attachment for CMC components
FR3108672B1 (fr) * 2020-03-24 2023-06-02 Safran Aircraft Engines Ensemble d'anneau de turbine
FR3108867B1 (fr) * 2020-04-07 2022-04-15 Safran Aircraft Engines Moule pour la fabrication d’un carter de soufflante de turbomachine en matériau composite
FR3113696B1 (fr) * 2020-09-03 2023-02-24 Safran Aircraft Engines Pièce de turbomachine avec bord de liaison en matériau composite à matrice céramique et à fibres courtes et son procédé de fabrication
US11255210B1 (en) 2020-10-28 2022-02-22 Rolls-Royce Corporation Ceramic matrix composite turbine shroud assembly with joined cover plate
US11346251B1 (en) * 2021-05-25 2022-05-31 Rolls-Royce Corporation Turbine shroud assembly with radially biased ceramic matrix composite shroud segments
US11761351B2 (en) * 2021-05-25 2023-09-19 Rolls-Royce Corporation Turbine shroud assembly with radially located ceramic matrix composite shroud segments
US11629607B2 (en) 2021-05-25 2023-04-18 Rolls-Royce Corporation Turbine shroud assembly with radially and axially biased ceramic matrix composite shroud segments
US11346237B1 (en) 2021-05-25 2022-05-31 Rolls-Royce Corporation Turbine shroud assembly with axially biased ceramic matrix composite shroud segment
US11286812B1 (en) 2021-05-25 2022-03-29 Rolls-Royce Corporation Turbine shroud assembly with axially biased pin and shroud segment
US11441441B1 (en) 2021-06-18 2022-09-13 Rolls-Royce Corporation Turbine shroud with split pin mounted ceramic matrix composite blade track
US11319828B1 (en) 2021-06-18 2022-05-03 Rolls-Royce Corporation Turbine shroud assembly with separable pin attachment
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FR3142504A1 (fr) * 2022-11-24 2024-05-31 Safran Ceramics Ensemble de turbine pour une turbomachine
US11773751B1 (en) 2022-11-29 2023-10-03 Rolls-Royce Corporation Ceramic matrix composite blade track segment with pin-locating threaded insert
US11840936B1 (en) 2022-11-30 2023-12-12 Rolls-Royce Corporation Ceramic matrix composite blade track segment with pin-locating shim kit
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US11732604B1 (en) 2022-12-01 2023-08-22 Rolls-Royce Corporation Ceramic matrix composite blade track segment with integrated cooling passages
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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WO2015108658A1 (fr) * 2014-01-17 2015-07-23 General Electric Company Manchon de suspension en cmc pour enveloppe en cmc

Also Published As

Publication number Publication date
WO2017103411A2 (fr) 2017-06-22
CN109072705B (zh) 2021-02-09
CN109072705A (zh) 2018-12-21
FR3045716A1 (fr) 2017-06-23
FR3045716B1 (fr) 2018-01-26
US20180363506A1 (en) 2018-12-20
US10378385B2 (en) 2019-08-13
EP3390782B1 (fr) 2019-11-27
EP3390782A2 (fr) 2018-10-24

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