EP1099826B1 - Dispositif de fixation pour une virole de turbine - Google Patents
Dispositif de fixation pour une virole de turbine Download PDFInfo
- Publication number
- EP1099826B1 EP1099826B1 EP00403105A EP00403105A EP1099826B1 EP 1099826 B1 EP1099826 B1 EP 1099826B1 EP 00403105 A EP00403105 A EP 00403105A EP 00403105 A EP00403105 A EP 00403105A EP 1099826 B1 EP1099826 B1 EP 1099826B1
- 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.)
- Expired - Lifetime
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 an assembly particular between a turbine ring, having for function of bordering the turbine delineating the vein of gas flow, and a part called 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 connecting pieces of ring 3 to the spacer 2 comprise, on the upstream side, a hook of spacer 4 and a ring hook 5 which are nested one inside the other: the assembly of the ring 3 is produced by pressing the end of the hook 5 in the hollow of the spacer hook 4, then by rotating the ring 3 to approach his opposite end, downstream from that of the spacer 2; the other 6 assembly parts are located on these downstream ends.
- the tenon presents two flanges 10 and 11, radially directed towards inside and that come up against the bottom of the mortise 9.
- Clips 12 are then fixed over the parallel ends of the flanges 7 and 8, so that its branches 13 and 14 enclose them and prevent them from disjoining themselves.
- the disjunction between the spacer 2 and the ring 3 is also prohibited by nesting hooks 4 and 5 on the other side; the ring 3 can play slightly in the axial direction on the spacer 2, inside a race whose length is defined by the total clearance between the flanks flanges 10 and 11 and the flanks of the mortise 9, at the places marked with references 15 and 16.
- This axial clearance creates an air leak downstream of the system. It is therefore important to reduce it as much as possible.
- the minimum value must be respected to preserve the rocking assembly of the ring.
- the ring 3 For make a good seal on the downstream hook, the ring 3 must be plated: its facing side must press on the collar 10. For this, the collar 10 is locally deformed in axial direction to cause this tightening. So, this punctual clamping system allows both to ensure the axial clearance necessary for the rocker and a seal by support.
- the invention relates to an assembly perfected between a turbine ring and its spacer, in which the principles of this prior assembly (fixation in radial direction by nested hooks on one side, and by abutment faces of flanges on the other side; and limitation of axial movement by a tenon system mortise on this other side), but which is superior in regarding the cohesion of the adjustment, the spacer protection against overheating excessive and mechanical strength.
- the tenon now belongs to the ring, and the mortise to the spacer, and that the tenon and mortise are separated from the abutment faces on the edges of the spacer and the ring, and placed behind the portions of these ledges that carry the stop faces.
- the spacer 2 is usually made of a material easier to machine, which allows to easily create the mortise, for example in forming a tongue, which helps to surround the mortise in connection with an adjoining part of the spacer.
- the tongue can be sufficiently flexible to be deformed and lock the tenon in good conditions and perform axial clamping for get a flat seal.
- the tenon and the mortise thus offer a resistance to gas leaks between the chamber inside and the circulation vein. It then becomes possible in good conditions to dissociate spacer and ring flanges on the essentials of their length and keep only a small area stop, instead of the two flanges 10 and 11 spaced from the previous conception: heat transfers from ring 3 to spacer 2 are then smaller.
- the staples that hold the flanges tight can see their soul lodged in nicks of these edges, which does not affect the watertightness of assembly since the edges would have been separated at the place of the cuts; but pushing the souls of staples to the cuts, it prevents them from protruding outside the edges and thus reduces the congestion of the whole; moreover, the staples now serve to limit slippage angular rings on the spacers, butting against the side faces of the cuts. So we can remove the pawns from the previous achievement 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 form.
- the hook of the ring 3 can cover the spacer hook, contrary to the design earlier, 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 the realization known, here bear the respective references 102 and 103. They are conventionally formed of abutting segments along a circumference, and segments of the ring 103 have discarded 30 disc seals between segments to limit gas flow in the radial and axial directions. Room inner 31 similar to the 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 stem 36 coming in front its end 34 and a tip 37 coming in front of the rod 33; the hooks are thus reversed in relation to the anterior design, but their assembly by nesting remains the same.
- the spacer 102 and the ring 103 are provided with flanges 38 and 39 which extend parallel to the downstream like the edges 7 and 8 of the design previous, but here the flange 38 of the spacer 102 includes only a flange 40 which establishes the stop with the rim 39; the flanges 38 and 39 are separated over most of their length of a game 57.
- the tightening of the ring 103 on the spacer 102 in axial direction is due to a stud 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 delimited by the rim 38 and especially by a bent tab 43, built on the back side of this rim 38.
- the last 44 of the tongue 43 is flexible, which allows the fold when editing is done, to remove the play in the axial direction of the tenon 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 functioning, when dilations and vibrations difficult to evaluate affected the assembly.
- a seal 55 may be inserted into a throat 56 dug into one of the flanges 39, at the location stop 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)
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) et 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 (41) et une mortaise (42) de rétention axiale façonnés sur l'anneau et l'entretoise, le tenon étant engagé dans la mortaise, caractérisé en ce que le tenon (41) et la mortaise (42) sont situés en amont des rebords en butée.
- Assemblage selon la revendication 1, caractérisé en ce que la mortaise (42) est délimitée par une languette (43) flexible de l'entretoise, le tenon (41) 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 (41) et la mortaise (42) 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 EP1099826A1 (fr) | 2001-05-16 |
EP1099826B1 true 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 (1)
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---|---|---|---|---|
EP4170237A1 (fr) * | 2021-10-21 | 2023-04-26 | Raytheon Technologies Corporation | Joint à languette comprenant un canal d'accouplement pour refroidissement |
Families Citing this family (53)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
DE102005013797A1 (de) | 2005-03-24 | 2006-09-28 | Alstom Technology Ltd. | Wärmestausegment |
DE102005013796A1 (de) * | 2005-03-24 | 2006-09-28 | Alstom Technology Ltd. | Wärmestausegment |
DE102005013798A1 (de) * | 2005-03-24 | 2006-09-28 | Alstom Technology Ltd. | Wärmestausegment zum Abdichten eines Strömungskanals einer Strömungsrotationsmaschine |
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 |
US7600967B2 (en) * | 2005-07-30 | 2009-10-13 | United Technologies Corporation | Stator assembly, module and method for forming a rotary machine |
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 |
EP1939459B1 (fr) | 2006-12-27 | 2018-04-25 | Safran Aero Boosters SA | Système de raccordement avec mâchoires de deux viroles, notamment d'un compresseur |
FR2921410B1 (fr) * | 2007-09-24 | 2010-03-12 | Snecma | Organe de verrouillage de secteurs d'anneau sur un carter de turbomachine, comprenant des moyens permettant sa prehension |
FR2923527B1 (fr) | 2007-11-13 | 2013-12-27 | Snecma | Etage de turbine ou de compresseur, en particulier de turbomachine |
FR2923528B1 (fr) * | 2007-11-13 | 2009-12-11 | Snecma | Etage de turbine ou de compresseur d'un turboreacteur |
FR2923526B1 (fr) * | 2007-11-13 | 2013-12-13 | Snecma | Etage de turbine ou de compresseur de turbomachine |
FR2931196B1 (fr) * | 2008-05-16 | 2010-06-18 | Snecma | Organe de verrouillage de secteurs d'anneau sur un carter de turbomachine, comprenant des passages radiaux permettant sa prehension |
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 |
FR2942845B1 (fr) * | 2009-03-09 | 2011-04-01 | Snecma | Ensemble d'anneau de turbine |
JP5646517B2 (ja) * | 2009-03-09 | 2014-12-24 | スネクマ | タービンリング組立体 |
FR2942844B1 (fr) * | 2009-03-09 | 2014-06-27 | Snecma | Ensemble d'anneau de turbine avec arret axial |
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 |
FR2955359B1 (fr) * | 2010-01-21 | 2013-07-19 | Snecma | Etancheite amont d'un anneau en cmc d'un etage de turbine |
FR2955898B1 (fr) * | 2010-02-02 | 2012-10-26 | Snecma | Etancheite amont d'un anneau en cmc dans une turbine de turbomachine |
FR2957093B1 (fr) * | 2010-03-02 | 2012-03-23 | Snecma | Preforme fibreuse pour un secteur d'anneau de turbine et son procede de fabrication. |
EP2977618B1 (fr) * | 2011-12-31 | 2019-10-30 | Rolls-Royce Corporation | Moteur à turbine à gaz ayant une virole et procédé de montage associé |
US20130272870A1 (en) * | 2012-04-17 | 2013-10-17 | General Electric Company | Mica-based seals for gas turbine shroud retaining clip |
US10344621B2 (en) * | 2012-04-27 | 2019-07-09 | General Electric Company | System and method of limiting axial movement between components in a turbine assembly |
BR112014025448A2 (pt) * | 2012-04-27 | 2017-11-28 | Gen Electric | grampo retentor, moldura de turbina e método de limitação. |
CA2870713C (fr) | 2012-04-27 | 2017-02-14 | General Electric Company | Ensemble carenage et joint d'etancheite pour moteur de turbine a gaz |
EP2719867B1 (fr) | 2012-10-12 | 2015-01-21 | MTU Aero Engines GmbH | Structure de boîtier avec étanchéification et refroidissement améliorés |
FR3009739B1 (fr) * | 2013-08-13 | 2015-09-11 | Snecma | Amelioration pour le verrouillage de pieces de support d'aubage |
FR3009740B1 (fr) | 2013-08-13 | 2017-12-15 | Snecma | Amelioration pour le verrouillage de pieces de support d'aubage |
EP2846001B1 (fr) * | 2013-09-06 | 2023-01-11 | MTU Aero Engines AG | Procédés de montage et de démontage d'un rotor d'une turbine à gaz, et outil associé |
US9932901B2 (en) | 2015-05-11 | 2018-04-03 | General Electric Company | Shroud retention system with retention springs |
US9828879B2 (en) * | 2015-05-11 | 2017-11-28 | General Electric Company | Shroud retention system with keyed retention clips |
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 |
FR3070718B1 (fr) * | 2017-09-06 | 2019-08-23 | Safran Aircraft Engines | Ensemble de turbine a secteurs d'anneau |
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 |
Family Cites Families (7)
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 |
US5641267A (en) * | 1995-06-06 | 1997-06-24 | General Electric Company | Controlled leakage shroud panel |
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 |
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 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 ES ES00403105T patent/ES2232397T3/es not_active Expired - Lifetime
- 2000-11-09 CA CA002359049A patent/CA2359049C/fr not_active Expired - Fee Related
- 2000-11-09 EP EP00403105A patent/EP1099826B1/fr not_active Expired - Lifetime
- 2000-11-09 KR KR1020017008681A patent/KR100724779B1/ko not_active IP Right Cessation
- 2000-11-09 RU RU2001122340/06A patent/RU2256082C2/ru not_active IP Right Cessation
- 2000-11-09 US US09/868,902 patent/US6575697B1/en not_active Expired - Lifetime
- 2000-11-09 DE DE60017676T patent/DE60017676T2/de not_active Expired - Lifetime
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP4170237A1 (fr) * | 2021-10-21 | 2023-04-26 | Raytheon Technologies Corporation | Joint à languette comprenant un canal d'accouplement pour refroidissement |
US11933221B2 (en) | 2021-10-21 | 2024-03-19 | Rtx Corporation | Tongue joint including mating channel for cooling |
Also Published As
Publication number | Publication date |
---|---|
RU2256082C2 (ru) | 2005-07-10 |
DE60017676T2 (de) | 2005-12-29 |
KR20010089800A (ko) | 2001-10-08 |
JP2003514182A (ja) | 2003-04-15 |
JP4181323B2 (ja) | 2008-11-12 |
WO2001034946A1 (fr) | 2001-05-17 |
US6575697B1 (en) | 2003-06-10 |
EP1099826A1 (fr) | 2001-05-16 |
FR2800797B1 (fr) | 2001-12-07 |
CA2359049A1 (fr) | 2001-05-17 |
KR100724779B1 (ko) | 2007-06-04 |
CA2359049C (fr) | 2009-01-13 |
FR2800797A1 (fr) | 2001-05-11 |
ES2232397T3 (es) | 2005-06-01 |
DE60017676D1 (de) | 2005-03-03 |
UA67818C2 (uk) | 2004-07-15 |
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