FR3027341B1 - ROTARY ASSEMBLY FOR TURBOMACHINE INCLUDING A SELF-PROPORTED ROTOR CRANKSET - Google Patents
ROTARY ASSEMBLY FOR TURBOMACHINE INCLUDING A SELF-PROPORTED ROTOR CRANKSET Download PDFInfo
- 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
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
- 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
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- 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
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- 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)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (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.
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 |
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 |
US15/519,351 US20170226861A1 (en) | 2014-10-15 | 2015-10-15 | Rotary assembly for a turbine engine comprising a self-supported rotor collar |
CN201580062098.6A CN107002690B (en) | 2014-10-15 | 2015-10-15 | Rotating assembly for a turbine engine comprising a self-supporting rotor casing |
EP15804160.8A EP3207221B1 (en) | 2014-10-15 | 2015-10-15 | Rotating assembly for turbomachine and turbomachine |
BR112017007761-2A BR112017007761B1 (en) | 2014-10-15 | 2015-10-15 | ROTATING ASSEMBLY FOR A TURBOMACHINE AND TURBOMACHINE |
PCT/FR2015/052776 WO2016059348A1 (en) | 2014-10-15 | 2015-10-15 | Rotary assembly for a turbine engine comprising a self-supported rotor collar |
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 (6)
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 |
FR3120092A1 (en) * | 2021-02-24 | 2022-08-26 | Safran Aircraft Engines | Impeller sealing ring |
FR3126014A1 (en) * | 2021-08-05 | 2023-02-10 | Safran Aircraft Engines | Distributor for turbomachinery |
Family Cites Families (5)
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 |
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2014
- 2014-10-15 FR FR1459889A patent/FR3027341B1/en active Active
Also Published As
Publication number | Publication date |
---|---|
FR3027341A1 (en) | 2016-04-22 |
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Legal Events
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PLFP | Fee payment |
Year of fee payment: 2 |
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Effective date: 20160422 |
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CD | Change of name or company name |
Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170717 |
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