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FR3027341B1 - ROTARY ASSEMBLY FOR TURBOMACHINE INCLUDING A SELF-PROPORTED ROTOR CRANKSET - Google Patents

ROTARY ASSEMBLY FOR TURBOMACHINE INCLUDING A SELF-PROPORTED ROTOR CRANKSET Download PDF

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Publication number
FR3027341B1
FR3027341B1 FR1459889A FR1459889A FR3027341B1 FR 3027341 B1 FR3027341 B1 FR 3027341B1 FR 1459889 A FR1459889 A FR 1459889A FR 1459889 A FR1459889 A FR 1459889A FR 3027341 B1 FR3027341 B1 FR 3027341B1
Authority
FR
France
Prior art keywords
rotor
stator
stage
consecutive
rotary 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.)
Active
Application number
FR1459889A
Other languages
French (fr)
Other versions
FR3027341A1 (en
Inventor
Gael Frederic Claude Cyrille Evain
Pierre-Louis Alexandre Carlos
Claire Charlotte Groleau
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
SNECMA 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
Priority to FR1459889A priority Critical patent/FR3027341B1/en
Application filed by SNECMA SAS filed Critical SNECMA SAS
Priority to CA2966126A priority patent/CA2966126C/en
Priority to US15/519,351 priority patent/US20170226861A1/en
Priority to PCT/FR2015/052776 priority patent/WO2016059348A1/en
Priority to EP15804160.8A priority patent/EP3207221B1/en
Priority to RU2017115405A priority patent/RU2712560C2/en
Priority to CN201580062098.6A priority patent/CN107002690B/en
Priority to BR112017007761-2A priority patent/BR112017007761B1/en
Publication of FR3027341A1 publication Critical patent/FR3027341A1/en
Application granted granted Critical
Publication of FR3027341B1 publication Critical patent/FR3027341B1/en
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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical
    • 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]
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

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

Abstract

Le présent exposé concerne un ensemble rotatif pour turbomachine permettant un meilleur contrôle du jeu radial entre deux pièces coaxiales. Il comprend un rotor comportant au moins deux étages rotoriques consécutifs (10a, 10b) munis d'une pluralité d'aubes mobiles (20), et une virole de rotor (50), annulaire, reliant lesdits deux étages rotoriques consécutifs (10a, 10b); un stator comportant au moins un étage statorique (11), muni d'une pluralité d'aubes fixes (30), prévu entre lesdits deux étages rotoriques consécutifs (10a, 10b), et un anneau de stator (60), annulaire, monté sur lesdites aubes fixes (30) ; l'un (50) des éléments parmi la virole de rotor et l'anneau de stator porte au moins une léchette (51) configurée pour coopérer avec une piste abradable (62) portée par l'autre (60) desdits éléments ; la virole de rotor (50) comporte, à chacune de ses extrémités amont et aval, soit une portion de contact du type axial (52, 53) s'étendant au-dessous d'une butée (71, 72) de l'étage rotorique correspondant, soit une portion de contact du type oblique reposant sur une surface d'appui oblique de l'étage rotorique correspondant.This disclosure relates to a rotary assembly for a turbomachine allowing better control of the radial clearance between two coaxial parts. It comprises a rotor comprising at least two consecutive rotor stages (10a, 10b) provided with a plurality of mobile vanes (20), and a rotor shell (50), annular, connecting said two consecutive rotor stages (10a, 10b ); a stator comprising at least one stator stage (11), provided with a plurality of fixed vanes (30), provided between said two consecutive rotor stages (10a, 10b), and a stator ring (60), annular, mounted on said fixed vanes (30); one (50) of the elements among the rotor ferrule and the stator ring carries at least one wiper (51) configured to cooperate with an abradable track (62) carried by the other (60) of said elements; the rotor shell (50) comprises, at each of its upstream and downstream ends, either a contact portion of the axial type (52, 53) extending below a stop (71, 72) of the stage corresponding rotor, or a contact portion of the oblique type resting on an oblique bearing surface of the corresponding rotor stage.

FR1459889A 2014-10-15 2014-10-15 ROTARY ASSEMBLY FOR TURBOMACHINE INCLUDING A SELF-PROPORTED ROTOR CRANKSET Active FR3027341B1 (en)

Priority Applications (8)

Application Number Priority Date Filing Date Title
FR1459889A FR3027341B1 (en) 2014-10-15 2014-10-15 ROTARY ASSEMBLY FOR TURBOMACHINE INCLUDING A SELF-PROPORTED ROTOR CRANKSET
US15/519,351 US20170226861A1 (en) 2014-10-15 2015-10-15 Rotary assembly for a turbine engine comprising a self-supported rotor collar
PCT/FR2015/052776 WO2016059348A1 (en) 2014-10-15 2015-10-15 Rotary assembly for a turbine engine comprising a self-supported rotor collar
EP15804160.8A EP3207221B1 (en) 2014-10-15 2015-10-15 Rotating assembly for turbomachine and turbomachine
CA2966126A CA2966126C (en) 2014-10-15 2015-10-15 Rotary assembly for a turbine engine comprising a self-supported rotor collar
RU2017115405A RU2712560C2 (en) 2014-10-15 2015-10-15 Rotary assembly for turbine engine comprising self-supporting rotor casing
CN201580062098.6A CN107002690B (en) 2014-10-15 2015-10-15 Rotating assembly for a turbine engine comprising a self-supporting rotor casing
BR112017007761-2A BR112017007761B1 (en) 2014-10-15 2015-10-15 ROTATING ASSEMBLY FOR A TURBOMACHINE AND TURBOMACHINE

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1459889A FR3027341B1 (en) 2014-10-15 2014-10-15 ROTARY ASSEMBLY FOR TURBOMACHINE INCLUDING A SELF-PROPORTED ROTOR CRANKSET

Publications (2)

Publication Number Publication Date
FR3027341A1 FR3027341A1 (en) 2016-04-22
FR3027341B1 true FR3027341B1 (en) 2020-10-23

Family

ID=52824303

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1459889A Active FR3027341B1 (en) 2014-10-15 2014-10-15 ROTARY ASSEMBLY FOR TURBOMACHINE INCLUDING A SELF-PROPORTED ROTOR CRANKSET

Country Status (1)

Country Link
FR (1) FR3027341B1 (en)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3067405B1 (en) 2017-06-13 2020-08-14 Safran Aircraft Engines TURBOMACHINE AND PROCESS FOR SEALING BY AIR BLOWING
FR3075253B1 (en) * 2017-12-20 2019-11-22 Safran Aircraft Engines SHOCK ABSORBER DEVICE
FR3080646B1 (en) * 2018-04-26 2020-03-27 Safran Aircraft Engines SEALING BETWEEN A FIXED WHEEL AND A MOBILE WHEEL OF A TURBOMACHINE
BE1027025B1 (en) * 2019-02-04 2020-09-02 Safran Aero Boosters Sa HYBRID ROTOR WITH SEGMENTED DRUM
FR3096722B1 (en) * 2019-05-29 2021-12-03 Safran Aircraft Engines Dynamic gasket for turbomachine comprising a multilayer abradable part
FR3120092A1 (en) 2021-02-24 2022-08-26 Safran Aircraft Engines Impeller sealing ring
FR3126014B1 (en) * 2021-08-05 2024-06-14 Safran Aircraft Engines Distributor for turbomachine

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2825748B1 (en) * 2001-06-07 2003-11-07 Snecma Moteurs TURBOMACHINE ROTOR ARRANGEMENT WITH TWO BLADE DISCS SEPARATED BY A SPACER
US8177495B2 (en) * 2009-03-24 2012-05-15 General Electric Company Method and apparatus for turbine interstage seal ring
US8608436B2 (en) * 2010-08-31 2013-12-17 General Electric Company Tapered collet connection of rotor components
US9540940B2 (en) * 2012-03-12 2017-01-10 General Electric Company Turbine interstage seal system
DE102012014109A1 (en) * 2012-07-17 2014-01-23 Rolls-Royce Deutschland Ltd & Co Kg Washer seal for use in gas turbine engine, has sealing ring, which is arranged between radially outer sections of rotor disks and is clamped between rotor disks in axial direction, where sealing elements are arranged on sealing ring

Also Published As

Publication number Publication date
FR3027341A1 (en) 2016-04-22

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