EP1099826A1 - Dispositif de fixation pour une virole de turbine - Google Patents
Dispositif de fixation pour une virole de turbine Download PDFInfo
- Publication number
- EP1099826A1 EP1099826A1 EP00403105A EP00403105A EP1099826A1 EP 1099826 A1 EP1099826 A1 EP 1099826A1 EP 00403105 A EP00403105 A EP 00403105A EP 00403105 A EP00403105 A EP 00403105A EP 1099826 A1 EP1099826 A1 EP 1099826A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- spacer
- ring
- mortise
- tenon
- hook
- 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.)
- Granted
Links
Images
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
-
- 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
- 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
- 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
Definitions
- This invention is part of an assembly particular between a turbine ring, having for function to border the turbine by delimiting the vein gas flow, and a piece called a spacer which belongs to the structure of the turbine.
- a modern assembly is described in the patent American 5,197,853 and illustrated in Figure 4.
- a body turbine 1 carries a spacer 2 which carries itself a ring 3.
- the assembly parts of ring 3 to spacer 2 include, on the upstream side, a hook spacer 4 and a ring hook 5 which are nested one inside the other: mounting the ring 3 is produced by pushing the end of the hook ring 5 in the hollow of the spacer hook 4, then by rotating the ring 3 to approach its opposite end, located downstream from that of the spacer 2; the other 6 assembly parts are located on these downstream ends.
- flange ring 8 It is a ledge of spacer 7 first radially inward, then downstream, and a ring flange 8 directed radially towards outside then axially downstream; the flange ring 8 is shaped into a mortise 9 in which accommodates part of the spacer flange 7, which plays thus the role of tenon.
- the post has two flanges 10 and 11, directed radially towards the interior and which come up against the bottom of the mortise 9. Staples 12 are then fixed over the parallel ends of the flanges 7 and 8, so that its branches 13 and 14 enclose them and keep them from falling apart.
- This axial clearance creates an air leak downstream of the system. It is therefore important to reduce it as much as possible. A minimum value must however be observed so to preserve the tilting assembly of the ring.
- ring 3 For perform a good seal on the downstream hook, ring 3 must be plated: its opposite face must press on the collar 10. For this, the collar 10 is locally deformed in an axial direction to cause this tightening. So this point tightening system allows both to ensure the axial clearance necessary for the tilting and sealing by pressing.
- the invention relates to an assembly perfected between a turbine ring and its spacer, in which we substantially resume the principles of this previous assembly (fixing in radial direction by hooks nested on one side, and by abutment faces of flanges on another side; and limitation of axial movement by a tenon system mortise on this other side), but which is superior in with regard to the cohesion of the adjustment, the protection of the spacer against overheating excessive and mechanical strength.
- the post now belongs to the ring, and the mortise to the spacer, and that the tenon and mortise are separated from the stop faces on the edges of the spacer and the ring, and placed behind the portions of these edges which carry the stop faces.
- the spacer 2 is generally made of a material that is easier to machine, which allows you to easily create the mortise, for example by shaping a tongue, which helps to surround the mortise in conjunction with an adjoining part of the spacer.
- the tongue may be sufficiently flexible to be deformed and lock the post in good conditions and perform axial tightening to obtain a plane seal.
- the tenon and the mortise thus offer a resistance to gas leaks between the chamber interior and circulation vein. It then becomes possible under good conditions to separate the spacer and ring edges on most of their length and keep only a small area stop, instead of the two flanges 10 and 11 spaced from the previous conception: heat transmissions from ring 3 to spacer 2 are then more reduced.
- the clips that keep the edges tight can see their soul lodged in gashes of these edges, which does not affect the waterproofness of assembly since the edges would have been separated at the location of the cuts; but pushing the souls of staples to the notches, they avoid protruding outside the edges and we reduce the overall size; in addition, the staples are now used to limit the sliding movement angle of the rings on the spacers, abutting against the lateral faces of the notches. So we can remove the pawns from the previous realization and their holes which were the seat of concentrations significant constraints.
- the cuts are also responsible for stress concentrations, but who are less important because of their size and of their more regular shape.
- the hook of the ring 3 can cover the spacer hook, unlike the design which again has the advantage of locally protect the spacer from overheating produced by the vein.
- the spacer and the ring whose general shape of each remains similar to that of achievement known, here bear the respective references 102 and 103. They are conventionally formed of butted segments along a circumference, and the segments of the ring 103 carry discarded strip seals 30 between segments to limit gas flows in the radial and axial directions. Room interior 31 similar to chamber 17 is delimited by the spacer 102 and the ring 103.
- the spacer 102 On the upstream side, the spacer 102 carries a hook 32 whose rod 33, extending radially inwards, gives on the chamber 31 and whose end 34 extends upstream; the hook 35 of the ring 103 extends outside the previous and covers it, with a rod 36 coming in front its tip 34 and a tip 37 coming in front of the rod 33; the hooks are thus reversed with respect to the earlier design but their assembly by nesting remains the same.
- the spacer 102 and the ring 103 are provided with edges 38 and 39 which extend parallel to downstream like edges 7 and 8 of the design front, but here the edge 38 of the spacer 102 includes only a flange 40 which establishes the stop with rim 39; edges 38 and 39 are separated over most of their length of a set 57.
- the tightening of the ring 103 on the spacer 102 in axial direction is due to a pin 41 established on the ring 103 and located behind the rim 38 of the spacer 102, on the side of the chamber 31; this tenon is retained in a mortise 42 bounded by the ledge 38 and above all by a curved tongue 43, built on the rear face of this rim 38.
- the end 44 of the tongue 43 is flexible, which allows the fold when mounting is done, to remove the axial play of the stud 41 between the flange 38 and the tongue 43; the low rigidity of the tip 44 allows to introduce only moderate constraints, which are not likely to become excessive during operation, when dilations and vibrations difficult to assess affected the assembly.
- a seal 55 can be inserted into a groove 56 dug in one of the edges 39, at the place abutment faces, to complete the seal.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Gasket Seals (AREA)
Abstract
Description
- la figure 1 est une vue générale de l'invention,
- la figure 2 est un détail de la figure 1,
- la figure 3 est une vue en perspective des pièces de la figure 2,
- et la figure 4, déjà décrite, illustre l'art antérieur.
Claims (6)
- Assemblage entre un anneau de turbine (103) bordant une entretoise (102) de structure de turbine (101) comprenant, à un côté amont, un crochet d'anneau (35) et un crochet d'entretoise (32) qui sont imbriqués et, à un côté aval, un système de jonction comprenant un rebord d'entretoise (38) et un rebord d'anneau (39) en butée, et enserrés par des agrafes (45) et un tenon et une mortaise de rétention axiale façonnés sur l'anneau et l'entretoise, le tenon étant engagé dans la mortaise, caractérisé en ce que le tenon et la mortaise sont situés en amont des rebords en butée.
- Assemblage selon la revendication 1, caractérisé en ce que la mortaise est délimitée par une languette (43) flexible de l'entretoise, le tenon étant engagé dans la mortaise avec un jeu nul.
- Assemblage selon la revendication 2, caractérisé en ce que le rebord d'entretoise (38) et le rebord de butée (39) sont en butée sur une partie de leur longueur et séparés d'un jeu sur une autre partie de leur longueur.
- Assemblage selon la revendication 3, caractérisé en ce que les rebords (38, 39) sont munis d'entailles (48, 49) en regard recevant une âme (50) des agrafes (45).
- Assemblage selon l'une quelconque des revendications 1 à 4, caractérisé en ce que le tenon et la mortaise donnent dans une chambre intérieure délimitée par l'entretoise et par l'anneau.
- Assemblage selon l'une quelconque des revendications 1 à 5, caractérisé en ce que le crochet de l'anneau (39) couvre le crochet de l'entretoise (32).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9914103A FR2800797B1 (fr) | 1999-11-10 | 1999-11-10 | Assemblage d'un anneau bordant une turbine a la structure de turbine |
FR9914103 | 1999-11-10 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1099826A1 true EP1099826A1 (fr) | 2001-05-16 |
EP1099826B1 EP1099826B1 (fr) | 2005-01-26 |
Family
ID=9551941
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP00403105A Expired - Lifetime EP1099826B1 (fr) | 1999-11-10 | 2000-11-09 | Dispositif de fixation pour une virole de turbine |
Country Status (11)
Country | Link |
---|---|
US (1) | US6575697B1 (fr) |
EP (1) | EP1099826B1 (fr) |
JP (1) | JP4181323B2 (fr) |
KR (1) | KR100724779B1 (fr) |
CA (1) | CA2359049C (fr) |
DE (1) | DE60017676T2 (fr) |
ES (1) | ES2232397T3 (fr) |
FR (1) | FR2800797B1 (fr) |
RU (1) | RU2256082C2 (fr) |
UA (1) | UA67818C2 (fr) |
WO (1) | WO2001034946A1 (fr) |
Cited By (20)
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---|---|---|---|---|
WO2006100233A1 (fr) * | 2005-03-24 | 2006-09-28 | Alstom Technology Ltd | Segment d'accumulation de chaleur |
WO2006100235A1 (fr) * | 2005-03-24 | 2006-09-28 | Alstom Technology Ltd | Segment d'accumulation de chaleur servant a rendre etanche un canal d'ecoulement d'une turbomachine |
WO2006100237A1 (fr) * | 2005-03-24 | 2006-09-28 | Alstom Technology Ltd | Segment d'accumulation de chaleur |
WO2007016220A2 (fr) * | 2005-07-30 | 2007-02-08 | United Technologies Corporation | Ensemble stator, module et procédé de formation d’une machine rotative |
EP1939459A1 (fr) * | 2006-12-27 | 2008-07-02 | Techspace aero | Système de raccordement avec mâchoires de deux viroles, notamment d'un compresseur |
EP2039885A1 (fr) * | 2007-09-24 | 2009-03-25 | Snecma | Organe de verrouillage de secteurs d'anneau sur un carter de turbomachine, comprenant des moyens permettant sa prehension |
FR2923526A1 (fr) * | 2007-11-13 | 2009-05-15 | Snecma Sa | Etage de turbine ou de compresseur de turbomachine |
FR2923527A1 (fr) * | 2007-11-13 | 2009-05-15 | Snecma Sa | Etage de turbine ou de compresseur, en particulier de turbomachine |
FR2942845A1 (fr) * | 2009-03-09 | 2010-09-10 | Snecma | Ensemble d'anneau de turbine |
FR2942844A1 (fr) * | 2009-03-09 | 2010-09-10 | Snecma | Ensemble d'anneau de turbine avec arret axial |
WO2010103213A1 (fr) * | 2009-03-09 | 2010-09-16 | Snecma | Ensemble d'anneau de turbine |
FR2955359A1 (fr) * | 2010-01-21 | 2011-07-22 | Snecma | Etancheite amont d'un anneau en cmc d'un etage de turbine |
FR2955898A1 (fr) * | 2010-02-02 | 2011-08-05 | Snecma | Etancheite amont d'un anneau en cmc dans une turbine de turbomachine |
EP2653662A1 (fr) * | 2012-04-17 | 2013-10-23 | General Electric Company | Joints au mica pour clip de retenue de carénage de turbine à gaz |
RU2498088C2 (ru) * | 2008-05-16 | 2013-11-10 | Снекма | Крепежная секция для устройства крепления кольцевых секторов на корпусе газотурбинного двигателя, устройство крепления кольцевых секторов на корпусе газотурбинного двигателя, турбина газотурбинного двигателя и газотурбинный двигатель |
WO2015022468A1 (fr) * | 2013-08-13 | 2015-02-19 | Snecma | Amelioration pour le verrouillage de pieces de support d'aubage |
FR3009739A1 (fr) * | 2013-08-13 | 2015-02-20 | Snecma | Amelioration pour le verrouillage de pieces de support d'aubage |
EP3093455A1 (fr) * | 2015-05-11 | 2016-11-16 | General Electric Company | Système de rétention de carénage avec des clips de retenue clavetés |
US9932901B2 (en) | 2015-05-11 | 2018-04-03 | General Electric Company | Shroud retention system with retention springs |
FR3070718A1 (fr) * | 2017-09-06 | 2019-03-08 | Safran Aircraft Engines | Ensemble de turbine a secteurs d'anneau |
Families Citing this family (34)
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FR2815668B1 (fr) * | 2000-10-19 | 2003-01-10 | Snecma Moteurs | Agencement de liaison d'un anneau de stator de turbine a une entretoise de support |
FR2816352B1 (fr) * | 2000-11-09 | 2003-01-31 | Snecma Moteurs | Ensemble de ventilation d'un anneau de stator |
FR2852053B1 (fr) | 2003-03-06 | 2007-12-28 | Snecma Moteurs | Turbine haute pression pour turbomachine |
US6997673B2 (en) * | 2003-12-11 | 2006-02-14 | Honeywell International, Inc. | Gas turbine high temperature turbine blade outer air seal assembly |
FR2869070B1 (fr) * | 2004-04-15 | 2008-10-17 | Snecma Moteurs Sa | Anneau de turbine |
FR2885168A1 (fr) * | 2005-04-27 | 2006-11-03 | Snecma Moteurs Sa | Dispositif d'etancheite pour une enceinte d'une turbomachine, et moteur d'aeronef equipe de celui-ci |
FR2887920B1 (fr) * | 2005-06-29 | 2010-09-10 | Snecma | Dispositif de fixation de secteurs d'anneau sur un carter de turbine |
JP4786362B2 (ja) * | 2006-02-14 | 2011-10-05 | 三菱重工業株式会社 | ケーシングおよび流体機械 |
FR2923528B1 (fr) * | 2007-11-13 | 2009-12-11 | Snecma | Etage de turbine ou de compresseur d'un turboreacteur |
FR2931195B1 (fr) * | 2008-05-16 | 2014-05-30 | Snecma | Organe dissymetrique de verrouillage de secteurs d'anneau sur un carter de turbomachine |
FR2931197B1 (fr) * | 2008-05-16 | 2010-06-18 | Snecma | Organe de verrouillage de secteurs d'anneau sur un carter de turbomachine, comprenant des passages axiaux pour sa prehension |
US8118548B2 (en) * | 2008-09-15 | 2012-02-21 | General Electric Company | Shroud for a turbomachine |
FR2941488B1 (fr) * | 2009-01-28 | 2011-09-16 | Snecma | Anneau de turbine a encoche anti-rotation |
FR2952965B1 (fr) * | 2009-11-25 | 2012-03-09 | Snecma | Isolation d'un rebord circonferentiel d'un carter externe de turbomachine vis-a-vis d'un secteur d'anneau correspondant |
FR2957093B1 (fr) | 2010-03-02 | 2012-03-23 | Snecma | Preforme fibreuse pour un secteur d'anneau de turbine et son procede de fabrication. |
WO2013102171A2 (fr) * | 2011-12-31 | 2013-07-04 | Rolls-Royce Corporation | Ensemble sillage des pales, composants et procédés |
JP5906357B2 (ja) * | 2012-04-27 | 2016-04-20 | ゼネラル・エレクトリック・カンパニイ | 分割フェアリングの部位間の径方向の移動の抑制に用いられる保持クリップおよび方法 |
EP2841720B1 (fr) * | 2012-04-27 | 2020-08-19 | General Electric Company | Système et procédé pour limiter le mouvement axial entre un étrier et un ensemble carénage dans un ensemble turbine |
WO2013163505A1 (fr) * | 2012-04-27 | 2013-10-31 | General Electric Company | Ensemble carénage et joint d'étanchéité pour moteur de turbine à gaz |
EP2719867B1 (fr) | 2012-10-12 | 2015-01-21 | MTU Aero Engines GmbH | Structure de boîtier avec étanchéification et refroidissement améliorés |
ES2935815T3 (es) * | 2013-09-06 | 2023-03-10 | MTU Aero Engines AG | (Des)montaje de un rotor de una turbina de gas, en particular delantero |
FR3036436B1 (fr) * | 2015-05-22 | 2020-01-24 | Safran Ceramics | Ensemble d'anneau de turbine avec maintien par brides |
FR3036433B1 (fr) * | 2015-05-22 | 2019-09-13 | Safran Ceramics | Ensemble d'anneau de turbine avec maintien par crabotage |
US10450895B2 (en) * | 2016-04-22 | 2019-10-22 | United Technologies Corporation | Stator arrangement |
US10697314B2 (en) | 2016-10-14 | 2020-06-30 | Rolls-Royce Corporation | Turbine shroud with I-beam construction |
FR3064022B1 (fr) * | 2017-03-16 | 2019-09-13 | Safran Aircraft Engines | Ensemble d'anneau de turbine |
RU2657404C1 (ru) * | 2017-06-16 | 2018-06-13 | Публичное акционерное общество "ОДК - Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Разъемный корпус турбомашины |
US10557365B2 (en) | 2017-10-05 | 2020-02-11 | Rolls-Royce Corporation | Ceramic matrix composite blade track with mounting system having reaction load distribution features |
DE102018210597A1 (de) * | 2018-06-28 | 2020-01-02 | MTU Aero Engines AG | Leitschaufelanordnung für eine strömungsmaschine |
US10934876B2 (en) * | 2018-07-18 | 2021-03-02 | Raytheon Technologies Corporation | Blade outer air seal AFT hook retainer |
US10634010B2 (en) | 2018-09-05 | 2020-04-28 | United Technologies Corporation | CMC BOAS axial retaining clip |
US11021987B2 (en) * | 2019-05-15 | 2021-06-01 | Raytheon Technologies Corporation | CMC BOAS arrangement |
US11149563B2 (en) | 2019-10-04 | 2021-10-19 | Rolls-Royce Corporation | Ceramic matrix composite blade track with mounting system having axial reaction load distribution features |
US11933221B2 (en) * | 2021-10-21 | 2024-03-19 | Rtx Corporation | Tongue joint including mating channel for cooling |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5197853A (en) | 1991-08-28 | 1993-03-30 | General Electric Company | Airtight shroud support rail and method for assembling in turbine engine |
US5320486A (en) * | 1993-01-21 | 1994-06-14 | General Electric Company | Apparatus for positioning compressor liner segments |
US5609469A (en) * | 1995-11-22 | 1997-03-11 | United Technologies Corporation | Rotor assembly shroud |
US5669757A (en) * | 1995-11-30 | 1997-09-23 | General Electric Company | Turbine nozzle retainer assembly |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5641267A (en) * | 1995-06-06 | 1997-06-24 | General Electric Company | Controlled leakage shroud panel |
FR2780443B1 (fr) * | 1998-06-25 | 2000-08-04 | Snecma | Anneau de stator de turbine haute pression d'une turbomachine |
US6435820B1 (en) * | 1999-08-25 | 2002-08-20 | General Electric Company | Shroud assembly having C-clip retainer |
-
1999
- 1999-11-10 FR FR9914103A patent/FR2800797B1/fr not_active Expired - Fee Related
-
2000
- 2000-09-11 UA UA2001074775A patent/UA67818C2/uk unknown
- 2000-11-09 CA CA002359049A patent/CA2359049C/fr not_active Expired - Fee Related
- 2000-11-09 DE DE60017676T patent/DE60017676T2/de not_active Expired - Lifetime
- 2000-11-09 RU RU2001122340/06A patent/RU2256082C2/ru not_active IP Right Cessation
- 2000-11-09 KR KR1020017008681A patent/KR100724779B1/ko not_active IP Right Cessation
- 2000-11-09 ES ES00403105T patent/ES2232397T3/es not_active Expired - Lifetime
- 2000-11-09 JP JP2001536854A patent/JP4181323B2/ja not_active Expired - Fee Related
- 2000-11-09 WO PCT/FR2000/003126 patent/WO2001034946A1/fr active Application Filing
- 2000-11-09 US US09/868,902 patent/US6575697B1/en not_active Expired - Lifetime
- 2000-11-09 EP EP00403105A patent/EP1099826B1/fr not_active Expired - Lifetime
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5197853A (en) | 1991-08-28 | 1993-03-30 | General Electric Company | Airtight shroud support rail and method for assembling in turbine engine |
US5320486A (en) * | 1993-01-21 | 1994-06-14 | General Electric Company | Apparatus for positioning compressor liner segments |
US5609469A (en) * | 1995-11-22 | 1997-03-11 | United Technologies Corporation | Rotor assembly shroud |
US5669757A (en) * | 1995-11-30 | 1997-09-23 | General Electric Company | Turbine nozzle retainer assembly |
Cited By (42)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7665957B2 (en) | 2005-03-24 | 2010-02-23 | Alstom Technology Ltd | Heat shield for sealing a flow channel of a turbine engine |
WO2006100235A1 (fr) * | 2005-03-24 | 2006-09-28 | Alstom Technology Ltd | Segment d'accumulation de chaleur servant a rendre etanche un canal d'ecoulement d'une turbomachine |
WO2006100237A1 (fr) * | 2005-03-24 | 2006-09-28 | Alstom Technology Ltd | Segment d'accumulation de chaleur |
US7665958B2 (en) | 2005-03-24 | 2010-02-23 | Alstom Technology Ltd. | Heat accumulation segment |
US7658593B2 (en) | 2005-03-24 | 2010-02-09 | Alstom Technology Ltd | Heat accumulation segment |
WO2006100233A1 (fr) * | 2005-03-24 | 2006-09-28 | Alstom Technology Ltd | Segment d'accumulation de chaleur |
KR101259205B1 (ko) * | 2005-03-24 | 2013-04-29 | 알스톰 테크놀러지 리미티드 | 열축적 세그먼트 |
WO2007016220A2 (fr) * | 2005-07-30 | 2007-02-08 | United Technologies Corporation | Ensemble stator, module et procédé de formation d’une machine rotative |
WO2007016220A3 (fr) * | 2005-07-30 | 2007-05-18 | United Technologies Corp | Ensemble stator, module et procédé de formation d’une machine rotative |
US8182216B2 (en) | 2006-12-27 | 2012-05-22 | Techspace Aero | Connecting system with jaws of two ferrules, including a compressor |
EP1939459A1 (fr) * | 2006-12-27 | 2008-07-02 | Techspace aero | Système de raccordement avec mâchoires de deux viroles, notamment d'un compresseur |
FR2921410A1 (fr) * | 2007-09-24 | 2009-03-27 | Snecma Sa | Organe de verrouillage de secteurs d'anneau sur un carter de turbomachine, comprenant des moyens permettant sa prehension |
US8038393B2 (en) | 2007-09-24 | 2011-10-18 | Snecma | Member for locking ring sectors onto a turbomachine casing, comprising means allowing it to be grasped |
EP2039885A1 (fr) * | 2007-09-24 | 2009-03-25 | Snecma | Organe de verrouillage de secteurs d'anneau sur un carter de turbomachine, comprenant des moyens permettant sa prehension |
EP2060750A1 (fr) * | 2007-11-13 | 2009-05-20 | Snecma | Etage de turbine ou de compresseur, en particulier de turbomachine |
US8133013B2 (en) | 2007-11-13 | 2012-03-13 | Snecma | Stage of a turbine or compressor, particularly for a turbomachine |
FR2923526A1 (fr) * | 2007-11-13 | 2009-05-15 | Snecma Sa | Etage de turbine ou de compresseur de turbomachine |
US8277179B2 (en) | 2007-11-13 | 2012-10-02 | Snecma | Turbine or compressor stage for a turbomachine |
FR2923527A1 (fr) * | 2007-11-13 | 2009-05-15 | Snecma Sa | Etage de turbine ou de compresseur, en particulier de turbomachine |
EP2060744A1 (fr) * | 2007-11-13 | 2009-05-20 | Snecma | Etage de turbine ou de compresseur de turbomachine |
RU2498088C2 (ru) * | 2008-05-16 | 2013-11-10 | Снекма | Крепежная секция для устройства крепления кольцевых секторов на корпусе газотурбинного двигателя, устройство крепления кольцевых секторов на корпусе газотурбинного двигателя, турбина газотурбинного двигателя и газотурбинный двигатель |
CN102272419A (zh) * | 2009-03-09 | 2011-12-07 | 斯奈克玛 | 涡轮环组件 |
US9080463B2 (en) | 2009-03-09 | 2015-07-14 | Snecma | Turbine ring assembly |
WO2010103213A1 (fr) * | 2009-03-09 | 2010-09-16 | Snecma | Ensemble d'anneau de turbine |
FR2942844A1 (fr) * | 2009-03-09 | 2010-09-10 | Snecma | Ensemble d'anneau de turbine avec arret axial |
FR2942845A1 (fr) * | 2009-03-09 | 2010-09-10 | Snecma | Ensemble d'anneau de turbine |
FR2955359A1 (fr) * | 2010-01-21 | 2011-07-22 | Snecma | Etancheite amont d'un anneau en cmc d'un etage de turbine |
FR2955898A1 (fr) * | 2010-02-02 | 2011-08-05 | Snecma | Etancheite amont d'un anneau en cmc dans une turbine de turbomachine |
EP2653662A1 (fr) * | 2012-04-17 | 2013-10-23 | General Electric Company | Joints au mica pour clip de retenue de carénage de turbine à gaz |
CN105579670A (zh) * | 2013-08-13 | 2016-05-11 | 斯奈克玛 | 叶片支撑部件的改进的锁定 |
FR3009740A1 (fr) * | 2013-08-13 | 2015-02-20 | Snecma | Amelioration pour le verrouillage de pieces de support d'aubage |
FR3009739A1 (fr) * | 2013-08-13 | 2015-02-20 | Snecma | Amelioration pour le verrouillage de pieces de support d'aubage |
WO2015022468A1 (fr) * | 2013-08-13 | 2015-02-19 | Snecma | Amelioration pour le verrouillage de pieces de support d'aubage |
US10247039B2 (en) | 2013-08-13 | 2019-04-02 | Safran Aircraft Engines | Locking of blade-supporting components |
EP3093455A1 (fr) * | 2015-05-11 | 2016-11-16 | General Electric Company | Système de rétention de carénage avec des clips de retenue clavetés |
US9828879B2 (en) | 2015-05-11 | 2017-11-28 | General Electric Company | Shroud retention system with keyed retention clips |
US9932901B2 (en) | 2015-05-11 | 2018-04-03 | General Electric Company | Shroud retention system with retention springs |
FR3070718A1 (fr) * | 2017-09-06 | 2019-03-08 | Safran Aircraft Engines | Ensemble de turbine a secteurs d'anneau |
WO2019048766A1 (fr) * | 2017-09-06 | 2019-03-14 | Safran Aircraft Engines | Ensemble de turbine à secteurs d'anneau |
CN111051649A (zh) * | 2017-09-06 | 2020-04-21 | 赛峰飞机发动机公司 | 具有环部段的涡轮组件 |
US11149574B2 (en) | 2017-09-06 | 2021-10-19 | Safran Aircraft Engines | Turbine assembly with ring segments |
CN111051649B (zh) * | 2017-09-06 | 2022-04-01 | 赛峰飞机发动机公司 | 具有环部段的涡轮组件 |
Also Published As
Publication number | Publication date |
---|---|
KR100724779B1 (ko) | 2007-06-04 |
JP4181323B2 (ja) | 2008-11-12 |
ES2232397T3 (es) | 2005-06-01 |
DE60017676T2 (de) | 2005-12-29 |
JP2003514182A (ja) | 2003-04-15 |
KR20010089800A (ko) | 2001-10-08 |
CA2359049A1 (fr) | 2001-05-17 |
WO2001034946A1 (fr) | 2001-05-17 |
UA67818C2 (uk) | 2004-07-15 |
RU2256082C2 (ru) | 2005-07-10 |
FR2800797B1 (fr) | 2001-12-07 |
DE60017676D1 (de) | 2005-03-03 |
FR2800797A1 (fr) | 2001-05-11 |
CA2359049C (fr) | 2009-01-13 |
EP1099826B1 (fr) | 2005-01-26 |
US6575697B1 (en) | 2003-06-10 |
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