FR3060051B1 - Turbine pour turbomachine - Google Patents

Turbine pour turbomachine Download PDF

Info

Publication number
FR3060051B1
FR3060051B1 FR1662442A FR1662442A FR3060051B1 FR 3060051 B1 FR3060051 B1 FR 3060051B1 FR 1662442 A FR1662442 A FR 1662442A FR 1662442 A FR1662442 A FR 1662442A FR 3060051 B1 FR3060051 B1 FR 3060051B1
Authority
FR
France
Prior art keywords
foil
radially outer
distributor
turbomachine
turbine
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
FR1662442A
Other languages
English (en)
Other versions
FR3060051A1 (fr
Inventor
Daniel Delaporte Nicolas
Pierre Beguin Anthony
Noel Durand Didier
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 FR1662442A priority Critical patent/FR3060051B1/fr
Publication of FR3060051A1 publication Critical patent/FR3060051A1/fr
Application granted granted Critical
Publication of FR3060051B1 publication Critical patent/FR3060051B1/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
    • 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
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • 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
    • F05D2230/72—Maintenance
    • 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
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
    • 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
    • F05D2260/37—Retaining components in desired mutual position by a press fit connection
    • 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
    • F05D2300/509—Self lubricating materials; Solid lubricants

Landscapes

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

Abstract

L'invention concerne une turbine pour turbomachine, notamment pour un turboréacteur ou un turbopropulseur d'avion, comportant : - un carter fixe (3), - un rotor comprenant des aubes dont la périphérie radialement externe comporte au moins une léchette (13a), apte à pivoter d'autour d'un axe, - un anneau (35) en matériau abradable entourant les aubes et coopérant avec les léchettes (13a), - un distributeur (11) comportant une plate-forme radialement externe (16), fixe par rapport au carter (3), - ledit anneau (35) comportant au moins une patte d'arrêt (44) en rotation, engagée dans un évidement (20) de forme complémentaire de la plate-forme radialement externe (16) du distributeur (11), caractérisée en ce qu'elle comporte au moins un clinquant (26) monté dans l'évidement (20), la patte d'arrêt (44) étant engagée dans le clinquant (26), les extrémités circonférentielles de ladite patte (44) étant aptes à venir en appui sur le clinquant (26).
FR1662442A 2016-12-14 2016-12-14 Turbine pour turbomachine Active FR3060051B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1662442A FR3060051B1 (fr) 2016-12-14 2016-12-14 Turbine pour turbomachine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1662442A FR3060051B1 (fr) 2016-12-14 2016-12-14 Turbine pour turbomachine
FR1662442 2016-12-14

Publications (2)

Publication Number Publication Date
FR3060051A1 FR3060051A1 (fr) 2018-06-15
FR3060051B1 true FR3060051B1 (fr) 2018-12-07

Family

ID=58162839

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1662442A Active FR3060051B1 (fr) 2016-12-14 2016-12-14 Turbine pour turbomachine

Country Status (1)

Country Link
FR (1) FR3060051B1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3084103B1 (fr) * 2018-07-18 2020-07-10 Safran Aircraft Engines Ensemble d'etancheite pour un rotor de turbine de turbomachine et turbine de turbomachine comprenant un tel ensemble

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8092163B2 (en) * 2008-03-31 2012-01-10 General Electric Company Turbine stator mount
FR2938872B1 (fr) * 2008-11-26 2015-11-27 Snecma Dispositif anti-usure pour aubes d'un distributeur de turbine d'une turbomachine aeronautique
FR2941488B1 (fr) * 2009-01-28 2011-09-16 Snecma Anneau de turbine a encoche anti-rotation
FR2986836B1 (fr) * 2012-02-09 2016-01-01 Snecma Tole annulaire anti-usure pour une turbomachine

Also Published As

Publication number Publication date
FR3060051A1 (fr) 2018-06-15

Similar Documents

Publication Publication Date Title
EP1840339B1 (fr) Dispositif de fixation de secteurs d'anneau autour d'une roue de turbine dans une turbomachine
CA2956882C (fr) Module de turbomachine
FR3083563B1 (fr) Module d'etancheite de turbomachine d'aeronef
FR3058756B1 (fr) Turbine pour turbomachine
EP3341570B1 (fr) Dispositif de fixation des rampes de refroidissement par jets d'air du carter d'une turbine de turbomachine
FR2989724A1 (fr) Etage de turbine pour une turbomachine
CA2518355A1 (fr) Retenue des clavettes de centrage des anneaux sous aubes de stator a calage variable d'un moteur a turbine a gaz
JP2012511663A5 (fr)
RU2016110757A (ru) Ротационное устройство для турбомашины
FR2985792A1 (fr) Secteur angulaire de redresseur a amortissement de vibrations par coin pour compresseur de turbomachine
FR3029960B1 (fr) Roue a aubes avec joint radial pour une turbine de turbomachine
FR3058755B1 (fr) Turbine pour turbomachine
FR3060051B1 (fr) Turbine pour turbomachine
FR3021706B1 (fr) Turbopropulseur d'aeronef comportant deux helices coaxiales.
FR3091725B1 (fr) Ensemble pour une turbomachine
RU2016123656A (ru) Компрессор газотурбинного двигателя, в частности турбовинтового или турбовентиляторного двигателя самолета
FR3072121B1 (fr) Dispositif d'etancheite entre rotor et stator de turbomachine
FR3071539B1 (fr) Joint d'etancheite a labyrinthe pour une turbomachine d'aeronef
FR3065745B1 (fr) Stator de turbomachine d'aeronef
FR3041714B1 (fr) Compresseur de turbomachine, en particulier de turbopropulseur ou de turboreacteur d'avion
FR3091553B1 (fr) Aube destinée à être montée sur un disque de rotor d’une turbomachine
FR3066176B1 (fr) Moyeu d'helice a motif deformable et systeme pour la detection d'anomalies affectant ledit moyeu
FR3006365A1 (fr) Roue de turbomachine, notamment pour turbine basse pression
EP3947918B1 (fr) Rotor de soufflante pour turbomachine
FR3103209B1 (fr) Joint d’étanchéité à labyrinthe comportant un élément abradable glissant

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 2

PLSC Publication of the preliminary search report

Effective date: 20180615

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

PLFP Fee payment

Year of fee payment: 7

PLFP Fee payment

Year of fee payment: 8