FR3099787B1 - Anneau pour une turbine de turbomachine ou de turbomoteur - Google Patents

Anneau pour une turbine de turbomachine ou de turbomoteur Download PDF

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Publication number
FR3099787B1
FR3099787B1 FR1908957A FR1908957A FR3099787B1 FR 3099787 B1 FR3099787 B1 FR 3099787B1 FR 1908957 A FR1908957 A FR 1908957A FR 1908957 A FR1908957 A FR 1908957A FR 3099787 B1 FR3099787 B1 FR 3099787B1
Authority
FR
France
Prior art keywords
ring
turbine
delimiting
radially
annular
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.)
Active
Application number
FR1908957A
Other languages
English (en)
Other versions
FR3099787A1 (fr
Inventor
Mathieu Laurent Herran
Yohan Smith
Bertrand Guillaume Robin Pellaton
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 Helicopter Engines SAS
Original Assignee
Safran Helicopter 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 Helicopter Engines SAS filed Critical Safran Helicopter Engines SAS
Priority to FR1908957A priority Critical patent/FR3099787B1/fr
Priority to PL20760497.6T priority patent/PL4010565T3/pl
Priority to PCT/FR2020/051433 priority patent/WO2021023945A1/fr
Priority to US17/630,454 priority patent/US20220251963A1/en
Priority to EP20760497.6A priority patent/EP4010565B1/fr
Priority to CN202080056482.6A priority patent/CN114207254A/zh
Publication of FR3099787A1 publication Critical patent/FR3099787A1/fr
Application granted granted Critical
Publication of FR3099787B1 publication Critical patent/FR3099787B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
    • 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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • 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

Abstract

L’invention concerne un anneau (1) pour une turbine de turbomachine, destiné à entourer une roue aubagée (2) d’un rotor de turbine, ledit anneau (1) s’étendant circonférentiellement autour d’un axe et comportant une partie de support annulaire (9), radialement externe, et une partie (10) délimitant une veine (6) de circulation d’un flux de gaz, radialement interne et comportant plusieurs segments (13) angulaires répartis sur la périphérie et situés de façon adjacente les uns par rapport aux autres de façon à former une partie annulaire délimitant la veine (6), des jeux circonférentiels (j) étant formés entre les extrémités circonférentielles des segments (13) adjacents situées en regard les unes des autres, chaque segment (13) étant relié à la partie de support (9) par l’intermédiaire d’une zone de liaison (14), un canal annulaire (15) de circulation de fluide de refroidissement étant délimité radialement entre la partie externe de support (9) et la partie interne (10) délimitant la veine. Figure à publier avec l’abrégé : Figure 1
FR1908957A 2019-08-05 2019-08-05 Anneau pour une turbine de turbomachine ou de turbomoteur Active FR3099787B1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
FR1908957A FR3099787B1 (fr) 2019-08-05 2019-08-05 Anneau pour une turbine de turbomachine ou de turbomoteur
PL20760497.6T PL4010565T3 (pl) 2019-08-05 2020-08-04 Pierścień do turbiny maszyny wirowej lub silnika turbinowego
PCT/FR2020/051433 WO2021023945A1 (fr) 2019-08-05 2020-08-04 Anneau pour une turbine de turbomachine ou de turbomoteur
US17/630,454 US20220251963A1 (en) 2019-08-05 2020-08-04 Ring for a turbomachine or a turboshaft engine turbine
EP20760497.6A EP4010565B1 (fr) 2019-08-05 2020-08-04 Anneau pour une turbine de turbomachine ou de turbomoteur
CN202080056482.6A CN114207254A (zh) 2019-08-05 2020-08-04 用于涡轮机涡轮或涡轮轴发动机涡轮的环

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1908957 2019-08-05
FR1908957A FR3099787B1 (fr) 2019-08-05 2019-08-05 Anneau pour une turbine de turbomachine ou de turbomoteur

Publications (2)

Publication Number Publication Date
FR3099787A1 FR3099787A1 (fr) 2021-02-12
FR3099787B1 true FR3099787B1 (fr) 2021-09-17

Family

ID=69375409

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1908957A Active FR3099787B1 (fr) 2019-08-05 2019-08-05 Anneau pour une turbine de turbomachine ou de turbomoteur

Country Status (6)

Country Link
US (1) US20220251963A1 (fr)
EP (1) EP4010565B1 (fr)
CN (1) CN114207254A (fr)
FR (1) FR3099787B1 (fr)
PL (1) PL4010565T3 (fr)
WO (1) WO2021023945A1 (fr)

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2659950B2 (ja) * 1987-03-27 1997-09-30 株式会社東芝 ガスタービンシユラウド
US5456576A (en) * 1994-08-31 1995-10-10 United Technologies Corporation Dynamic control of tip clearance
GB9725623D0 (en) * 1997-12-03 2006-09-20 Rolls Royce Plc Improvements in or relating to a blade tip clearance system
US6116852A (en) * 1997-12-11 2000-09-12 Pratt & Whitney Canada Corp. Turbine passive thermal valve for improved tip clearance control
FR2891300A1 (fr) * 2005-09-23 2007-03-30 Snecma Sa Dispositif de controle de jeu dans une turbine a gaz
GB0703827D0 (en) * 2007-02-28 2007-04-11 Rolls Royce Plc Rotor seal segment
DE102009016260A1 (de) * 2009-04-03 2010-10-07 Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. Verfahren beim Schweißen und Bauteil
US8753073B2 (en) * 2010-06-23 2014-06-17 General Electric Company Turbine shroud sealing apparatus
EP2728124B1 (fr) * 2012-10-30 2018-12-12 MTU Aero Engines AG Anneau de turbine et turbomachine
US10060288B2 (en) * 2015-10-09 2018-08-28 United Technologies Corporation Multi-flow cooling passage chamber for gas turbine engine
US10100654B2 (en) * 2015-11-24 2018-10-16 Rolls-Royce North American Technologies Inc. Impingement tubes for CMC seal segment cooling
US10480337B2 (en) * 2017-04-18 2019-11-19 Rolls-Royce North American Technologies Inc. Turbine shroud assembly with multi-piece seals

Also Published As

Publication number Publication date
PL4010565T3 (pl) 2024-02-19
EP4010565A1 (fr) 2022-06-15
FR3099787A1 (fr) 2021-02-12
CN114207254A (zh) 2022-03-18
EP4010565B1 (fr) 2023-10-18
WO2021023945A1 (fr) 2021-02-11
US20220251963A1 (en) 2022-08-11

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