FR3096394B1 - Ensemble pour turbomachine - Google Patents

Ensemble pour turbomachine Download PDF

Info

Publication number
FR3096394B1
FR3096394B1 FR1905427A FR1905427A FR3096394B1 FR 3096394 B1 FR3096394 B1 FR 3096394B1 FR 1905427 A FR1905427 A FR 1905427A FR 1905427 A FR1905427 A FR 1905427A FR 3096394 B1 FR3096394 B1 FR 3096394B1
Authority
FR
France
Prior art keywords
slot
adjacent
circumferential
turbomachine assembly
sealing strip
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
FR1905427A
Other languages
English (en)
Other versions
FR3096394A1 (fr
Inventor
Bruno Marc-Etienne Loisel
Etienne Léon Francois
Quentin Bruno Guy André Emile Lievoux
Vijeay Patel
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
Priority to FR1905427A priority Critical patent/FR3096394B1/fr
Publication of FR3096394A1 publication Critical patent/FR3096394A1/fr
Application granted granted Critical
Publication of FR3096394B1 publication Critical patent/FR3096394B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • 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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • 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
    • F05D2240/55—Seals
    • F05D2240/57—Leaf 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
    • F05D2250/71—Shape curved
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gasket Seals (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L’invention concerne un ensemble pour turbomachine comportant un distributeur annulaire sectorisé s’étendant autour d’un axe, lesdits secteurs (1) étant disposés circonférentiellement de façon adjacente de manière à former un anneau, les surfaces d’extrémité circonférentielle adjacentes (5) d’au moins un premier et un second secteurs adjacents (1) comportant respectivement une première fente et une seconde fente (7) destinées à l’insertion d’au moins une lamelle d’étanchéité (8) comportant une première zone d’extrémité circonférentielle (9) insérée dans la première fente (7) et une seconde zone d’extrémité circonférentielle (10) insérée dans la seconde fente (7), caractérisé en ce que ladite lamelle d’étanchéité (8) comporte au moins une zone médiane ondulée (11) déformable, située entre lesdites zones d’extrémité (9, 10).
FR1905427A 2019-05-23 2019-05-23 Ensemble pour turbomachine Active FR3096394B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1905427A FR3096394B1 (fr) 2019-05-23 2019-05-23 Ensemble pour turbomachine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1905427A FR3096394B1 (fr) 2019-05-23 2019-05-23 Ensemble pour turbomachine
FR1905427 2019-05-23

Publications (2)

Publication Number Publication Date
FR3096394A1 FR3096394A1 (fr) 2020-11-27
FR3096394B1 true FR3096394B1 (fr) 2021-05-28

Family

ID=67810886

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1905427A Active FR3096394B1 (fr) 2019-05-23 2019-05-23 Ensemble pour turbomachine

Country Status (1)

Country Link
FR (1) FR3096394B1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3126442B1 (fr) * 2021-08-25 2024-03-01 Safran Aircraft Engines Roue aubagée de stator de turbine

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1022437A1 (fr) * 1999-01-19 2000-07-26 Siemens Aktiengesellschaft Elément de construction à l'usage d'une machine thermique
FR2902843A1 (fr) * 2006-06-23 2007-12-28 Snecma Sa Secteur de redresseur de compresseur ou secteur de distributeur de turbomachine
EP2657455A1 (fr) * 2012-04-27 2013-10-30 Siemens Aktiengesellschaft Écran thermique et procédé de construction associé
FR3051015B1 (fr) 2016-05-09 2020-06-26 Safran Aircraft Engines Dispositif d'etancheite entre deux aubes successives
WO2018048390A1 (fr) * 2016-09-07 2018-03-15 Siemens Aktiengesellschaft Joint souple
FR3065986B1 (fr) * 2017-05-02 2021-07-09 Safran Aircraft Engines Ensemble pour turbine a gaz, turbine a gaz associee

Also Published As

Publication number Publication date
FR3096394A1 (fr) 2020-11-27

Similar Documents

Publication Publication Date Title
CL2021001419A1 (es) (divisional de solicitud 2091-2019) acoplamiento mécánico para la tubería estructural y mecánica.
KR20170093952A (ko) 밀봉 장치
FR3096394B1 (fr) Ensemble pour turbomachine
JP6254305B2 (ja) 室温において隙間の側面で互いに対して平坦に当接する２つの部材間の隙間を密封するための密封装置
US9752679B2 (en) Dual pre-load cylindrical seal
FR3070716B1 (fr) Languette d'etancheite de segments de stator
EP3499095A1 (fr) Segment de piston
US2333196A (en) Metallic packing ring for locomotive piston rods and the like
FR3078363B1 (fr) Anneau mobile d'etancheite
US2285961A (en) Piston ring and sealing means therefor
FR3072749B1 (fr) Train d'engrenages epicycloidal
FR3065986B1 (fr) Ensemble pour turbine a gaz, turbine a gaz associee
FR3126468B1 (fr) Joint annulaire d’étanchéité pour une turbomachine d’aéronef
FR3080168B1 (fr) Ensemble pour une chambre de combustion de turbomachine
FR3063103B1 (fr) Assemblage pour turbine a gaz, turbine a gaz associee
FR3079868B1 (fr) Lechette d'etancheite entre rotor et stator et turbine ainsi equipee
ATE278130T1 (de) Sekundärdichtungselement für eine gleitringdichtungsanordnung
FR3032255B1 (fr) Joint etanche uniquement apres sertissage
US1187811A (en) Piston-ring.
FR3065481B1 (fr) Ensemble pour turbine, notamment pour une turbomachine
FR3095833B1 (fr) Anneau d’etancheite pour une turbomachine d’aeronef
FR3109182B1 (fr) Ensemble d’etancheite pour une turbomachine
US1645146A (en) Piston ring
EP3800385A1 (fr) Élément d'étanchéité pour une tige axialement coulissante
FR3090729B1 (fr) Structure d’etancheite pour turbomachine

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 2

PLSC Publication of the preliminary search report

Effective date: 20201127

PLFP Fee payment

Year of fee payment: 3

PLFP Fee payment

Year of fee payment: 4

PLFP Fee payment

Year of fee payment: 5

PLFP Fee payment

Year of fee payment: 6