EP1199444A1 - Agencement de liaison d'un anneau de stator de turbine à une entretoise de support - Google Patents
Agencement de liaison d'un anneau de stator de turbine à une entretoise de support Download PDFInfo
- Publication number
- EP1199444A1 EP1199444A1 EP01402686A EP01402686A EP1199444A1 EP 1199444 A1 EP1199444 A1 EP 1199444A1 EP 01402686 A EP01402686 A EP 01402686A EP 01402686 A EP01402686 A EP 01402686A EP 1199444 A1 EP1199444 A1 EP 1199444A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- ring
- spacer
- notch
- lips
- tab
- 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
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
-
- 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
- F05D2240/00—Components
- F05D2240/10—Stators
Definitions
- the subject of this invention is a arrangement connecting a turbine stator ring to a spacer used to support this ring.
- Turbine stators often include rings, composed of a number of segments of arc of circle, and whose function is to delimit the gas circulation vein. These rings are supported and immobilized by connecting spacers to a main portion of the stator.
- the ring segments are mounted in the spacer by a hinge movement: the ring segments and the spacer have additional hooks on one side, which are likely to nest one in the other by establishing a seal thanks to a garnish ; they still wear lips on the side opposite, that we approach each other rotating the hooks.
- a bracket is installed to hold them in position tight. We strive to establish the seal on this side by direct contact with the surfaces of the lips, without use garnish.
- the spacer lip is divided into two portions circular and parallel, called rails, by a groove and is housed in a ring lip groove the same width as it, so that the faces outer side of the rails must establish sealing against the lateral faces of the groove ring.
- the reality is probably not so satisfactory since only a tightening of the rails in a slightly narrower ring groove would guarantee the maintenance of the sealing contact, but mounting the ring would then be too difficult.
- the ring groove is a little more wider than the spacer lip, which leaves remain clearances between the lateral faces and leaks.
- the lip clamping brackets having a short angular extension had their soul central unit engaged in aligned notches of lips: this made it possible to stop the sliding of the rotating ring but the adjustment of the stirrups in two cuts at once was difficult.
- the invention relates to a means improved to obtain a clamping of two flat faces sealing, directed axially, of the ring and the spacer.
- it concerns in its form most generally a connecting arrangement of a ring of turbine stator to an annular spacer of ring support, comprising, on a first side of ring and spacer, assembly hooks from the ring to the spacer and, on a second side of the ring and the spacer axially opposite the first side, sealing faces by mutual support axially directed and stirrups enclosing lips, concentric and near the faces seal, ring and spacer, characterized in that one of the lips comprises at minus a notch sinking in the axial direction and the other of the lips includes at least one leg curved penetrating into the notch, a bottom face notch bending the tab in a direction of reinforcement of the support of the sealing faces.
- Legs and notches can be any number to obtain the desired tightening. As they are executed in the contact lips, they do not increase the size of the ring or the spacer, and there follows the important advantage that legs and notches can be used to maintain the position of the rings in the spacers also in tangential direction, replacing engaged pawns in holes and used before to ensure this only function, but which required machining additional and weakened the structure.
- a spacer 1 circular of which only a portion of arc is shown, includes upper hooks 2 and 3 of attachment to a main portion, not shown, of stator and a lower hook 4 used for fixing of ring segments 5 by hooks 6 complementary on these.
- Spacer 1 and ring 5 bear again, on a side axially opposite the hooks 4 and 6, respective lips 7 and 8 intended to come in contact, spacer 1 and each ring segment 5 then including a cavity 9 between the hooks 4 and 6 and lips 7 and 8 which must be maintained sealing. It is achieved on the side of lips 7 and 8 maintaining contact between two planar faces 10 and 11, one located outside of a border 12 is standing on the ring 5 behind the lip 8, the other at the back of the lip 7 of the spacer 1. Legs 13, curved radially outwards, are provided in certain places of the lip 8 of the ring 5 and are used to push back the lip 7 of the spacer 1 against edge 12; lip 7 is a little wider that the space between the face 10 of the ring 5 and the tab 13.
- the tab 13 is relatively flexible and deforms so slightly when the lip 7 is introduced between it and the border 12.
- the tab 13 does not, however, support not on the outer edge of lip 7, but on a finger 14 protruding from the bottom of a notch 15 thereof and on the end 16 of which the tab 13 presses homogeneously.
- the finger 14 extends over a portion angularly in the middle of the notch 15.
- the width of the tab 13 can be adjusted relative to that of notch 15 to be inserted therein with positive or negative play, compatible with deflections whether tolerated or not towards tangential between spacer 1 and ring 5. None other material system, for example with pawn pushed into a hole, does not retain the ring on the spacer tangential direction.
- Figure 3 shows the bracket 18 used to join lips 7 and 8. It extends over the entire circumference covering the free edges of the lips 7 and 8 and legs 13 where they exist, without that no angular adjustment is necessary; and one regular tightening of the lips is obtained.
- the legs 13 could be in plurality on each segment ring 5; the tangential link could be ensured by the retention of a portion of the lip 7 spacer 5 between two legs 13 rather than by that of a tab 13 between two portions of the lip 7; or again, the legs 13 and notches 15 could be inverted and carried each by the other of lips.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gasket Seals (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Sealing Devices (AREA)
- Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
Abstract
Description
- la figure 1 est une vue générale de l'agencement de l'invention,
- la figure 2 est une vue de détail,
- et la figure 3 est une coupe représentant la mise en place de l'étrier.
Claims (4)
- Agencement de liaison d'un anneau (5) de stator de turbine à une entretoise (1) annulaire de support de l'anneau, comprenant, sur un premier côté de l'anneau et de l'entretoise, des crochets (4, 6) d'assemblage de l'anneau à l'entretoise et, sur un second côté de l'anneau et de l'entretoise opposé axialement au premier côté, des faces d'étanchéité (10, 11) par appui mutuel dirigées axialement et un étrier (18) enserrant des lèvres (7, 8), concentriques et voisines des faces d'étanchéité, de l'anneau et de l'entretoise, caractérisé en ce que l'une des lèvres comprend au moins une entaille (15) s'enfonçant en direction axiale et l'autre des lèvres comprend au moins une patte recourbée (13) pénétrant dans l'entaille, une face de fond de l'entaille faisant fléchir la patte dans un sens de renforcement de l'appui des faces d'étanchéité.
- Agencement selon la revendication 1, caractérisé en ce que le fond de l'entaille (15) comprend un doigt (14) qui fait saillie vers la patte dans une portion angulairement médiane de l'entaille.
- Agencement selon l'une quelconque des revendications 1 ou 2, caractérisé en ce que la patte et l'entaille ont des largeurs ajustées pour laisser subsister entre eux un jeu correspondant à une tolérance de débattement tangentiel de l'anneau dans l'entretoise, aucun autre système ne retenant par ailleurs l'anneau (5) dans l'entretoise (1) en direction angulaire.
- Agencement selon l'une quelconque des revendications 1 à 3, caractérisé en ce que l'étrier (18) couvre des bords libres des lèvres (7, 8).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0013355 | 2000-10-19 | ||
FR0013355A FR2815668B1 (fr) | 2000-10-19 | 2000-10-19 | Agencement de liaison d'un anneau de stator de turbine a une entretoise de support |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1199444A1 true EP1199444A1 (fr) | 2002-04-24 |
EP1199444B1 EP1199444B1 (fr) | 2006-08-09 |
Family
ID=8855481
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP01402686A Expired - Lifetime EP1199444B1 (fr) | 2000-10-19 | 2001-10-18 | Agencement de liaison d'un anneau de stator de turbine à une entretoise de support |
Country Status (8)
Country | Link |
---|---|
US (1) | US6699011B2 (fr) |
EP (1) | EP1199444B1 (fr) |
CA (1) | CA2359274C (fr) |
DE (1) | DE60122083T2 (fr) |
ES (1) | ES2265406T3 (fr) |
FR (1) | FR2815668B1 (fr) |
RU (1) | RU2276737C2 (fr) |
UA (1) | UA72509C2 (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2529825A1 (fr) | 2011-06-01 | 2012-12-05 | Alstom Technology Ltd | Capture de CO2 avec bouclage de carbonate |
Families Citing this family (27)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2887920B1 (fr) * | 2005-06-29 | 2010-09-10 | Snecma | Dispositif de fixation de secteurs d'anneau sur un carter de turbine |
US7438520B2 (en) * | 2005-08-06 | 2008-10-21 | General Electric Company | Thermally compliant turbine shroud mounting assembly |
US7452183B2 (en) * | 2005-08-06 | 2008-11-18 | General Electric Company | Thermally compliant turbine shroud assembly |
US7442004B2 (en) * | 2005-08-06 | 2008-10-28 | General Electric Company | Thermally compliant C-clip |
US20080025838A1 (en) * | 2006-07-25 | 2008-01-31 | Siemens Power Generation, Inc. | Ring seal for a turbine engine |
FR2923526B1 (fr) * | 2007-11-13 | 2013-12-13 | Snecma | Etage de turbine ou de compresseur de turbomachine |
FR2923527B1 (fr) * | 2007-11-13 | 2013-12-27 | Snecma | Etage de turbine ou de compresseur, en particulier 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 |
FR2941488B1 (fr) * | 2009-01-28 | 2011-09-16 | Snecma | Anneau de turbine a encoche anti-rotation |
US9726043B2 (en) | 2011-12-15 | 2017-08-08 | General Electric Company | Mounting apparatus for low-ductility turbine shroud |
US9051849B2 (en) * | 2012-02-13 | 2015-06-09 | United Technologies Corporation | Anti-rotation stator segments |
CA2870765C (fr) * | 2012-04-27 | 2017-03-28 | General Electric Company | Systeme et procede pour limiter le mouvement axial entre un etrier et un ensemble carenage dans un ensemble turbine |
EP2841716A1 (fr) | 2012-04-27 | 2015-03-04 | General Electric Company | Agrafe de retenue, carcasse de turbine et procédé de limitation de mouvement radial |
US9650905B2 (en) * | 2012-08-28 | 2017-05-16 | United Technologies Corporation | Singlet vane cluster assembly |
US10378387B2 (en) | 2013-05-17 | 2019-08-13 | General Electric Company | CMC shroud support system of a gas turbine |
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 |
EP3080403B1 (fr) | 2013-12-12 | 2019-05-01 | General Electric Company | Système de support de carénage cmc |
JP6574208B2 (ja) | 2014-06-12 | 2019-09-11 | ゼネラル・エレクトリック・カンパニイ | シュラウドハンガアセンブリ |
JP6775425B2 (ja) | 2014-06-12 | 2020-10-28 | ゼネラル・エレクトリック・カンパニイ | シュラウドハンガーアセンブリ |
CN106460560B (zh) | 2014-06-12 | 2018-11-13 | 通用电气公司 | 护罩吊架组件 |
JP5717904B1 (ja) * | 2014-08-04 | 2015-05-13 | 三菱日立パワーシステムズ株式会社 | 静翼、ガスタービン、分割環、静翼の改造方法、および、分割環の改造方法 |
US10378371B2 (en) * | 2014-12-18 | 2019-08-13 | United Technologies Corporation | Anti-rotation vane |
US9874104B2 (en) | 2015-02-27 | 2018-01-23 | General Electric Company | Method and system for a ceramic matrix composite shroud hanger assembly |
US10450895B2 (en) * | 2016-04-22 | 2019-10-22 | United Technologies Corporation | Stator arrangement |
PL3299591T3 (pl) * | 2016-09-27 | 2020-05-18 | Siemens Aktiengesellschaft | Nośnik łopatek prowadzących, obudowa turbiny oraz turbina |
KR101937586B1 (ko) * | 2017-09-12 | 2019-01-10 | 두산중공업 주식회사 | 베인 조립체, 터빈 및 이를 포함하는 가스터빈 |
DE102018210597A1 (de) * | 2018-06-28 | 2020-01-02 | MTU Aero Engines AG | Leitschaufelanordnung für eine strömungsmaschine |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4676715A (en) * | 1985-01-30 | 1987-06-30 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation | Turbine rings of gas turbine plant |
US4687413A (en) * | 1985-07-31 | 1987-08-18 | United Technologies Corporation | Gas turbine engine assembly |
EP0334794A2 (fr) * | 1988-03-23 | 1989-09-27 | United Technologies Corporation | Assemblage d'un stator pour une machine rotative à flux axiale |
US5018941A (en) * | 1989-01-11 | 1991-05-28 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation"S.N.E.C.M.A. | Blade fixing arrangement for a turbomachine rotor |
US5197853A (en) | 1991-08-28 | 1993-03-30 | General Electric Company | Airtight shroud support rail and method for assembling in turbine engine |
EP0945597A1 (fr) * | 1998-03-23 | 1999-09-29 | Asea Brown Boveri AG | Montage des aubes statoriques dans une installation de turbine à gas |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5205708A (en) * | 1992-02-07 | 1993-04-27 | General Electric Company | High pressure turbine component interference fit up |
US5593276A (en) * | 1995-06-06 | 1997-01-14 | General Electric Company | Turbine shroud hanger |
US5562408A (en) * | 1995-06-06 | 1996-10-08 | General Electric Company | Isolated turbine shroud |
FR2800797B1 (fr) * | 1999-11-10 | 2001-12-07 | Snecma | Assemblage d'un anneau bordant une turbine a la structure de turbine |
-
2000
- 2000-10-19 FR FR0013355A patent/FR2815668B1/fr not_active Expired - Fee Related
-
2001
- 2001-10-15 US US09/976,143 patent/US6699011B2/en not_active Expired - Lifetime
- 2001-10-17 CA CA002359274A patent/CA2359274C/fr not_active Expired - Lifetime
- 2001-10-18 UA UA2001107095A patent/UA72509C2/uk unknown
- 2001-10-18 RU RU2001128181/06A patent/RU2276737C2/ru active
- 2001-10-18 DE DE60122083T patent/DE60122083T2/de not_active Expired - Lifetime
- 2001-10-18 ES ES01402686T patent/ES2265406T3/es not_active Expired - Lifetime
- 2001-10-18 EP EP01402686A patent/EP1199444B1/fr not_active Expired - Lifetime
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4676715A (en) * | 1985-01-30 | 1987-06-30 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation | Turbine rings of gas turbine plant |
US4687413A (en) * | 1985-07-31 | 1987-08-18 | United Technologies Corporation | Gas turbine engine assembly |
EP0334794A2 (fr) * | 1988-03-23 | 1989-09-27 | United Technologies Corporation | Assemblage d'un stator pour une machine rotative à flux axiale |
US5018941A (en) * | 1989-01-11 | 1991-05-28 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation"S.N.E.C.M.A. | Blade fixing arrangement for a turbomachine rotor |
US5197853A (en) | 1991-08-28 | 1993-03-30 | General Electric Company | Airtight shroud support rail and method for assembling in turbine engine |
EP0945597A1 (fr) * | 1998-03-23 | 1999-09-29 | Asea Brown Boveri AG | Montage des aubes statoriques dans une installation de turbine à gas |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2529825A1 (fr) | 2011-06-01 | 2012-12-05 | Alstom Technology Ltd | Capture de CO2 avec bouclage de carbonate |
WO2012164370A1 (fr) | 2011-06-01 | 2012-12-06 | Alstom Technology Ltd | Capture de co2 utilisant une boucle de carbonate |
Also Published As
Publication number | Publication date |
---|---|
CA2359274C (fr) | 2010-01-05 |
CA2359274A1 (fr) | 2002-04-19 |
DE60122083T2 (de) | 2007-03-01 |
US20020048512A1 (en) | 2002-04-25 |
RU2276737C2 (ru) | 2006-05-20 |
FR2815668B1 (fr) | 2003-01-10 |
FR2815668A1 (fr) | 2002-04-26 |
US6699011B2 (en) | 2004-03-02 |
EP1199444B1 (fr) | 2006-08-09 |
DE60122083D1 (de) | 2006-09-21 |
UA72509C2 (uk) | 2005-03-15 |
ES2265406T3 (es) | 2007-02-16 |
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