EP1265033A1 - Chambre de combustion munie d'un système de fixation de fond de chambre - Google Patents
Chambre de combustion munie d'un système de fixation de fond de chambre Download PDFInfo
- Publication number
- EP1265033A1 EP1265033A1 EP02291362A EP02291362A EP1265033A1 EP 1265033 A1 EP1265033 A1 EP 1265033A1 EP 02291362 A EP02291362 A EP 02291362A EP 02291362 A EP02291362 A EP 02291362A EP 1265033 A1 EP1265033 A1 EP 1265033A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- combustion chamber
- axial
- chamber according
- fixed
- chamber
- 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
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/60—Support structures; Attaching or mounting means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2211/00—Thermal dilatation prevention or compensation
Definitions
- the present invention relates to the specific field of turbomachinery and it is more particularly interested in the problem posed by the mounting of a metal bottom of the combustion chamber of a turbomachine on walls made of CMC type composite material (ceramic matrix composite) from this room.
- the turbine high pressure including its inlet distributor (HPT nozzle), the system injection chamber, the combustion chamber and the annular casing of this chamber are made of metallic type materials.
- HPT nozzle inlet distributor
- the system injection chamber, the combustion chamber and the annular casing of this chamber are made of metallic type materials.
- CMC high temperature composite materials
- the difficulties of implementation and the cost of these materials make that their use is most often limited to the combustion chamber it even and more particularly with its only axial walls, the inlet distributor of the high pressure turbine, the injection system and the remaining annular casing then more conventionally made of metallic materials.
- the materials metallic and composite materials have coefficients of expansion very different thermal. This results in particularly acute problems especially at the connection between the composite material walls of the combustion chamber and the bottom of the metal chamber.
- the present invention overcomes these drawbacks by proposing an assembly of metal chamber bottom capable of absorbing induced displacements by the differences in the expansion coefficients between this metallic background and the composite walls of the combustion chamber.
- annular combustion chamber comprising external and internal axial walls of composite material and a bottom chamber of metallic material, characterized in that to allow a free radial expansion of said chamber bottom relative to said axial walls, said chamber bottom is held in position between said axial walls by a plurality of flexible tabs fixed on the one hand to said axial walls by fixing means and on the other hand to said chamber bottom by soldering or welding, said chamber bottom further comprising means for sealing between said chamber bottom and said axial walls.
- the flexible fixing tabs are made of a metallic material and the fixing means are constituted by a plurality of bolts, preferably captive nut.
- the sealing means comprise a seal circular type "lamellae" mounted in a circular groove of said bottom metal chamber and intended to ensure support on said axial wall of the combustion chamber opposite.
- the circular seal is sectorized and is kept in abutment against said axial wall by means of a elastic element fixed on said metal chamber bottom. This elastic element consists of a leaf spring.
- the sealing means comprise a circular segment mounted against said axial wall and intended to cooperate with a circular groove of said metal chamber bottom.
- this circular sealing segment is split.
- the flexible fixing tabs have a first end fixed to one or the other of said axial walls by said fixing means and a second end fixed by brazing or welding to the bottom of the chamber.
- the back of the room may include furthermore a metal crown on which the said arms are brazed or welded second ends of said flexible fixing tabs.
- the flexible fixing tabs have a first end fixed to one of said axial walls by first connecting means a second end fixed to the other of said walls axial by second connecting means and a central part fixed to the bottom of chamber by brazing or welding.
- these flexible tabs of fixing are arranged between each of the injection nozzles.
- the metal bottom 30 of the combustion chamber which has a coefficient of thermal expansion very different from that of the axial walls external 26 and internal 28 made of composite material of the combustion chamber, is fixedly held in position between these axial walls by a plurality of flexible tabs 36, 38 regularly distributed between the injection nozzles of fuel 22 (see for example Figure 4).
- These mounting tabs are mounted for a first series of them (see tab referenced 36) between the metal bottom 30 and the external axial wall 26 and for a second series of them (see the tab referenced 38) between the metal bottom 30 and the internal axial wall 28.
- Each flexible fixing tab is produced in a metallic material and preferably consists of a thin blade, width constant or not, having an attachment point at each of its two ends.
- first end 42; 44 of the fastening tab is fixed integrally and according to its location to one or the other of the axial walls external 26 or internal 28 of the combustion chamber by first means of attachment 46; 48 and the second end 50; 52 is preferably fixed by welding or solder to a metal crown 54; 56, itself brazed or welded to the metal chamber bottom 30 of the combustion chamber. This hanging allows the expansion of the chamber bottom without damaging the walls composite axles that move little radially.
- the first fixing means arranged in position offset from to the injection nozzles are advantageously of the bolt type. And to make it easier access as well as assembly / disassembly, these bolts are preferably chosen from captive nut type.
- the seal between the external or internal axial wall and the crown metallic is ensured by a circular seal of the "lamella" type 58; 60 mounted in a circular groove 62; 64 of the metal crown.
- This seal advantageously sectorized has in its upstream part a spoiler 66; 68 intended to ensure an O-ring support on the opposite axial wall 26; 28 of the combustion chamber.
- the seal is pressed against the wall by an element elastic 70; 72, preferably a leaf spring, and held in position by a plurality of pawns 74; 76 secured to the crown.
- Figure 2 illustrates a first alternative embodiment of the attachment of the metal chamber bottom on the axial walls in composite material of the combustion chamber, in which this chamber bottom and the crowns metal support of the fixing tabs are one piece 80 on which the second ends of the tabs 50; 52.
- This unique piece naturally includes the means previous sealing.
- FIGS. 3 and 4 A second variant is illustrated in FIGS. 3 and 4 in which it only one series of tabs 82 now exists, one end of which 84 is fixed to the external axial wall 26 by first connecting means 86 and a second end 88 is fixed to the internal axial wall 28 by second means 90.
- first and second connecting means are advantageously of bolt type.
- the tongue is also brazed (or welded) on the chamber bottom which can for example be formed by the single piece 80 of the aforementioned variant. This soldering is of course performed at the inter-injector spaces between the openings 32.
- Figure 5 illustrates a second embodiment (see also the detail of Figure Sa) in which the seal between the external axial wall 26 or internal 28 and the chamber bottom 30 is no longer ensured by a circular joint of the "to lamellae "but by a split (open) circular segment 92; 94 mounted tight against the axial wall, provided with a joint cover system and intended to cooperate with a circular groove 96; 98 of the metal crown 54, 56.
- the clearance at the bottom of the groove 96 for housing the outer segment 92 is calculated so that, in operation, the metal crown does not come into contact with the wall axial axial 26 of composite material, nor with the internal face 92a of the segment 92.
- the segment 94 of the internal wall is prestressed, the expansion at hot bottom of the chamber having the effect of detaching the bottom of the inner wall.
- the first end 42; 44 of the fixing tongue 36; 38 is fixed jointly and depending on its location at one or other of the external axial 26 or internal walls 28 of the combustion chamber by the first fixing means 46; 48 and the second end 50; 52 is preferably fixed by brazing or welding to the metal crown 54; 56, itself brazed or welded to the chamber bottom metal 30 of the combustion chamber.
- Figure 6 illustrates a first alternative embodiment of the above assembly in which the chamber bottom and the metal support crowns of the fixing tabs form only one piece 100 on which will be brazed or directly welded the second ends of these tabs 50; 52.
- This unique piece of course integrates the sealing means with segments precedents.
- a second variant is illustrated in Figure 7 in which it no longer exists that a single series of tabs 102, a first end 104 of which is fixed to the external axial wall 26 by first connecting means 106 and a second end 108 is fixed to the internal axial wall 28 by second means of link 110.
- first and second fixing means are advantageously of bolt type.
- the tongue is also brazed (or welded) on the chamber bottom which can, for example, be formed by the single piece 100 of the aforementioned variant. This soldering is of course performed at the inter-injector spaces between the openings 32.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Ceramic Engineering (AREA)
- Fuel-Injection Apparatus (AREA)
- Gasket Seals (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- la figure 1 est une vue schématique en demi-coupe axiale d'une partie d'injection d'une turbomachine incorporant un premier exemple de réalisation d'un assemblage selon l'invention,
- la figure la montre un détail de l'assemblage de la figure 1,
- la figure 2 est une vue schématique en demi-coupe axiale d'une partie d'injection d'une turbomachine incorporant une première variante du premier exemple de réalisation d'un assemblage selon l'invention,
- la figure 3 est une vue schématique en demi-coupe axiale d'une partie d'injection d'une turbomachine incorporant une seconde variante du premier exemple d'assemblage selon l'invention,
- la figure 4 est une partielle en bout illustrant la disposition alternée des buses d'injection et des languettes de fixation,
- la figure 5 est une vue schématique en demi-coupe axiale d'une partie d'injection d'une turbomachine incorporant un second exemple de réalisation d'un assemblage selon l'invention,
- la figure Sa montre un détail de l'assemblage de la figure 5,
- la figure 6 est une vue schématique en demi-coupe axiale d'une partie d'injection d'une turbomachine incorporant une première variante du second exemple d'assemblage selon l'invention, et
- la figure 7 est une vue schématique en demi-coupe axiale d'une partie d'injection d'une turbomachine incorporant une seconde variante du second exemple d'assemblage selon l'invention.
- une enveloppe annulaire externe (ou carter externe) 12, d'axe longitudinal 10,
- une enveloppe annulaire interne (ou carter interne) coaxiale 14,
- un espace annulaire 16 compris entre les deux enveloppes 12 et 14 recevant le
comburant comprimé, généralement de l'air, provenant en amont d'un
compresseur (non représenté) de la turbomachine, au travers d'un conduit
annulaire de diffusion 18 (on notera la présence de la grille de diffusion 18a)
définissant un flux général F d'écoulement des gaz,
cet espace 16 comportant, dans le sens d'écoulement des gaz, tout d'abord un ensemble d'injection formé d'une pluralité de systèmes d'injection 20 régulièrement répartis autour du conduit 18 et comportant chacun une buse d'injection de carburant 22 fixée sur l'enveloppe annulaire externe 12 (dans un souci de simplification des dessins les mélangeur et déflecteur associés à chaque buse d'injection ont été omis), ensuite une chambre de combustion annulaire 24, formée d'une paroi axiale externe 26 et d'une paroi axiale interne 28, toutes deux coaxiales d'axe 10 et réalisées en un matériau composite haute température, de type CMC ou autres (carbone par exemple), et d'une paroi transversale 30 réalisée en un matériau métallique, formant fond de chambre, et pourvue d'ouvertures 32 pour la fixation du système d'injection, et enfin un distributeur annulaire (non représenté) formant un étage d'entrée d'une turbine haute pression. Dans la réalisation illustrée, on notera la présence de la casquette interne 33 prolongeant vers l'amont (par rapport au flux F) la paroi interne 28 de la chambre de combustion. Une casquette externe 34 peut par contre être directement intégrée à la paroi externe 26 de cette chambre de combustion.
Claims (13)
- Chambre de combustion annulaire comportant des parois axiales externe (26) et interne (28) en matériau composite (24) et un fond de chambre (30, 80, 100) en matériau métallique (42), caractérisée en ce que pour permettre une libre dilatation radiale dudit fond de chambre par rapport auxdites parois axiales, ledit fond de chambre est maintenu en position entre lesdites parois axiales externe et interne par une pluralité de languettes souples (36, 38; 82; 102) fixée d'une part auxdites parois axiales par des moyens de fixation (46, 48; 86, 90; 106, 110) et d'autre part audit fond de chambre par brasure ou soudure, ledit fond de chambre comportant en outre des moyens (58, 60 ; 92, 94) pour assurer l'étanchéité entre ledit fond de chambre et lesdites parois axiales.
- Chambre de combustion selon la revendication 1, caractérisée en ce que lesdites languettes souples de fixation sont en un matériau métallique.
- Chambre de combustion selon la revendication 1, caractérisée en ce que lesdits moyens de fixation sont constitués par une pluralité de boulons, de préférence à écrou prisonnier.
- Chambre de combustion selon la revendication 1, caractérisée en ce que lesdits moyens d'étanchéité comportent un joint circulaire de type « à lamelles » (58, 60) monté dans une gorge circulaire (62, 64) dudit fond de chambre métallique et destiné à assurer un appui sur ladite paroi axiale de la chambre de combustion en regard (26, 28).
- Chambre de combustion selon la revendication 4, caractérisée en ce que ledit joint circulaire d'étanchéité est sectorisé.
- Chambre de combustion selon la revendication 4, caractérisée en ce que ledit joint circulaire d'étanchéité est maintenu en appui contre ladite paroi axiale au moyen d'un élément élastique (70, 72) fixé sur ledit fond de chambre métallique.
- Chambre de combustion selon la revendication 6, caractérisée en ce que ledit élément élastique est constitué par un ressort à lames.
- Chambre de combustion selon la revendication 1, caractérisée en ce que lesdits moyens d'étanchéité comportent un segment circulaire (92, 94) monté contre ladite paroi axiale et destiné à coopérer avec une gorge circulaire (96, 98) de ledit fond de chambre métallique.
- Chambre de combustion selon la revendication 8, caractérisée en ce que ledit segment circulaire d'étanchéité est fendu.
- Chambre de combustion selon la revendication 1, caractérisée en ce que les languettes souples de fixation (36, 38) comportent une première extrémité (42, 44) fixée à l'une ou l'autre desdites parois axiales par lesdits moyens de fixation et une seconde extrémité (50, 52) fixée par brasure ou soudure audit fond de chambre.
- Chambre de combustion selon la revendication 10, caractérisée en ce que ledit fond de chambre comporte en outre une couronne métallique (54, 56) sur laquelle sont brasées ou soudées lesdites secondes extrémités desdites languettes souples de fixation.
- Chambre de combustion selon la revendication 1, caractérisée en ce que les languettes souples de fixation (82, 102) comportent une première extrémité (84, 104) fixée à l'une desdites parois axiales par des premiers moyens de liaison (86, 106), une seconde extrémité (88, 108) fixée à l'autre desdites parois axiales par des seconds moyens de liaison (90, 110) et une partie centrale fixée au fond de chambre (80, 100) par brasure ou soudure.
- Chambre de combustion selon la revendication 12, caractérisée en ce que lesdites languettes souples de fixation sont disposées entre chacune des buses d'injection (22).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0107368A FR2825779B1 (fr) | 2001-06-06 | 2001-06-06 | Chambre de combustion munie d'un systeme de fixation de fond de chambre |
FR0107368 | 2001-06-06 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1265033A1 true EP1265033A1 (fr) | 2002-12-11 |
EP1265033B1 EP1265033B1 (fr) | 2008-10-22 |
Family
ID=8863991
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP02291362A Expired - Lifetime EP1265033B1 (fr) | 2001-06-06 | 2002-06-04 | Chambre de combustion munie d'un système de fixation de fond de chambre |
Country Status (5)
Country | Link |
---|---|
US (1) | US6647729B2 (fr) |
EP (1) | EP1265033B1 (fr) |
JP (1) | JP3967633B2 (fr) |
DE (1) | DE60229464D1 (fr) |
FR (1) | FR2825779B1 (fr) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2887015A1 (fr) * | 2005-06-14 | 2006-12-15 | Snecma Moteurs Sa | Assemblage d'une chambre de combustion annulaire de turbomachine |
FR2905166A1 (fr) * | 2006-08-28 | 2008-02-29 | Snecma Sa | Chambre de combustion annulaire d'une turbomachine. |
EP1903283A1 (fr) * | 2006-09-22 | 2008-03-26 | Snecma | Chambre de combustion annulaire d'une turbomachine |
EP1717516B1 (fr) * | 2005-04-28 | 2019-04-03 | Safran Aircraft Engines | Chambre de combustion aisément démontable à performance aérodynamique améliorée |
Families Citing this family (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2840974B1 (fr) * | 2002-06-13 | 2005-12-30 | Snecma Propulsion Solide | Anneau d'etancheite pour cahmbre de combustion et chambre de combustion comportant un tel anneau |
FR2855249B1 (fr) | 2003-05-20 | 2005-07-08 | Snecma Moteurs | Chambre de combustion ayant une liaison souple entre un fond de chambre et une paroi de chambre |
FR2871846B1 (fr) * | 2004-06-17 | 2006-09-29 | Snecma Moteurs Sa | Chambre de combustion en cmc de turbine a gaz supportee dans un carter metallique par des organes de liaison en cmc |
FR2871847B1 (fr) * | 2004-06-17 | 2006-09-29 | Snecma Moteurs Sa | Montage d'un distributeur de turbine sur une chambre de combustion a parois en cmc dans une turbine a gaz |
US20060030315A1 (en) * | 2004-08-06 | 2006-02-09 | Christopher Smith | Method and system for provisioning wireless services using SIM information |
FR2897418B1 (fr) * | 2006-02-10 | 2013-03-01 | Snecma | Chambre de combustion annulaire d'une turbomachine |
FR2897417A1 (fr) * | 2006-02-10 | 2007-08-17 | Snecma Sa | Chambre de combustion annulaire d'une turbomachine |
FR2897923B1 (fr) * | 2006-02-27 | 2008-06-06 | Snecma Sa | Chambre de combustion annulaire a fond amovible |
FR2931929B1 (fr) * | 2008-05-29 | 2010-06-04 | Snecma | Chambre de combustion annulaire de moteur a turbine a gaz |
FR2935753B1 (fr) * | 2008-09-08 | 2011-07-01 | Snecma Propulsion Solide | Liaisons souples a butee pour fixation de piece en cmc |
US8863527B2 (en) * | 2009-04-30 | 2014-10-21 | Rolls-Royce Corporation | Combustor liner |
WO2015038293A1 (fr) * | 2013-09-11 | 2015-03-19 | United Technologies Corporation | Chemise de chambre de combustion |
US10519794B2 (en) * | 2016-07-12 | 2019-12-31 | General Electric Company | Sealing system for sealing against a non-cylindrical surface |
US10393381B2 (en) * | 2017-01-27 | 2019-08-27 | General Electric Company | Unitary flow path structure |
US10247019B2 (en) | 2017-02-23 | 2019-04-02 | General Electric Company | Methods and features for positioning a flow path inner boundary within a flow path assembly |
US10731859B2 (en) | 2017-07-21 | 2020-08-04 | Delavan Inc. | Fuel nozzles |
US11525577B2 (en) | 2020-04-27 | 2022-12-13 | Raytheon Technologies Corporation | Extended bulkhead panel |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5142871A (en) * | 1991-01-22 | 1992-09-01 | General Electric Company | Combustor dome plate support having uniform thickness arcuate apex with circumferentially spaced coolant apertures |
EP0564183A1 (fr) * | 1992-03-30 | 1993-10-06 | General Electric Company | Chambre de combustion avec des aubes de dilution |
US5291732A (en) * | 1993-02-08 | 1994-03-08 | General Electric Company | Combustor liner support assembly |
US5479772A (en) * | 1992-06-12 | 1996-01-02 | General Electric Company | Film cooling starter geometry for combustor liners |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5457954A (en) * | 1993-12-21 | 1995-10-17 | Solar Turbines Inc | Rolling contact mounting arrangement for a ceramic combustor |
GB2295887A (en) * | 1994-12-08 | 1996-06-12 | Rolls Royce Plc | Combustor assembly |
JP3478531B2 (ja) * | 2000-04-21 | 2003-12-15 | 川崎重工業株式会社 | ガスタービンのセラミック部品支持構造 |
US6495207B1 (en) * | 2001-12-21 | 2002-12-17 | Pratt & Whitney Canada Corp. | Method of manufacturing a composite wall |
-
2001
- 2001-06-06 FR FR0107368A patent/FR2825779B1/fr not_active Expired - Fee Related
-
2002
- 2002-05-30 JP JP2002156755A patent/JP3967633B2/ja not_active Expired - Lifetime
- 2002-06-04 EP EP02291362A patent/EP1265033B1/fr not_active Expired - Lifetime
- 2002-06-04 DE DE60229464T patent/DE60229464D1/de not_active Expired - Lifetime
- 2002-06-05 US US10/161,653 patent/US6647729B2/en not_active Expired - Lifetime
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5142871A (en) * | 1991-01-22 | 1992-09-01 | General Electric Company | Combustor dome plate support having uniform thickness arcuate apex with circumferentially spaced coolant apertures |
EP0564183A1 (fr) * | 1992-03-30 | 1993-10-06 | General Electric Company | Chambre de combustion avec des aubes de dilution |
US5479772A (en) * | 1992-06-12 | 1996-01-02 | General Electric Company | Film cooling starter geometry for combustor liners |
US5291732A (en) * | 1993-02-08 | 1994-03-08 | General Electric Company | Combustor liner support assembly |
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1717516B1 (fr) * | 2005-04-28 | 2019-04-03 | Safran Aircraft Engines | Chambre de combustion aisément démontable à performance aérodynamique améliorée |
FR2887015A1 (fr) * | 2005-06-14 | 2006-12-15 | Snecma Moteurs Sa | Assemblage d'une chambre de combustion annulaire de turbomachine |
EP1734305A2 (fr) * | 2005-06-14 | 2006-12-20 | Snecma | Assemblage d'une chambre de combustion annulaire de turbomachine |
US7849696B2 (en) | 2005-06-14 | 2010-12-14 | Snecma | Assembling an annular combustion chamber of a turbomachine |
EP1734305A3 (fr) * | 2005-06-14 | 2013-05-01 | Snecma | Assemblage d'une chambre de combustion annulaire de turbomachine |
FR2905166A1 (fr) * | 2006-08-28 | 2008-02-29 | Snecma Sa | Chambre de combustion annulaire d'une turbomachine. |
EP1898155A1 (fr) * | 2006-08-28 | 2008-03-12 | Snecma | Chambre de combustion annulaire d'une turbomachine |
US8387395B2 (en) | 2006-08-28 | 2013-03-05 | Snecma | Annular combustion chamber for a turbomachine |
EP1903283A1 (fr) * | 2006-09-22 | 2008-03-26 | Snecma | Chambre de combustion annulaire d'une turbomachine |
FR2906350A1 (fr) * | 2006-09-22 | 2008-03-28 | Snecma Sa | Chambre de combustion annulaire d'une turbomachine |
US7971439B2 (en) | 2006-09-22 | 2011-07-05 | Snecma | Annular turbomachine combustion chamber |
RU2451242C2 (ru) * | 2006-09-22 | 2012-05-20 | Снекма | Кольцевая камера сгорания газотурбинного двигателя и газотурбинный двигатель |
Also Published As
Publication number | Publication date |
---|---|
EP1265033B1 (fr) | 2008-10-22 |
JP2002372241A (ja) | 2002-12-26 |
US20020184887A1 (en) | 2002-12-12 |
US6647729B2 (en) | 2003-11-18 |
FR2825779B1 (fr) | 2003-08-29 |
FR2825779A1 (fr) | 2002-12-13 |
DE60229464D1 (de) | 2008-12-04 |
JP3967633B2 (ja) | 2007-08-29 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP1265035B1 (fr) | Liaison de chambre de combustion CMC de turbomachine en deux parties | |
EP1265033B1 (fr) | Chambre de combustion munie d'un système de fixation de fond de chambre | |
EP1265034B1 (fr) | Accrochage de chambre de combustion CMC de turbomachine par pattes brasées | |
EP1265031B1 (fr) | Fixation de casquettes métalliques sur des parois de chambre de combustion CMC de turbomachine | |
EP1265037B1 (fr) | Accrochage de chambre de combustion CMC de turbomachine utilisant les trous de dilution | |
CA2577514C (fr) | Chambre de combustion annulaire d'une turbomachine | |
EP1734305B1 (fr) | Assemblage d'une chambre de combustion annulaire de turbomachine | |
EP1265036B1 (fr) | Montage élastique de chambre de combustion CMC de turbomachine dans un carter métallique | |
EP1265032B1 (fr) | Architecture de chambre de combustion de turbomachine en matériau à matrice céramique | |
EP1265030B1 (fr) | Accrochage de chambre de combustion CMC de turbomachine par viroles de liaison souples | |
EP2334909B1 (fr) | Etanchéité entre une chambre de combustion et un distributeur de turbine dans une turbomachine | |
WO2008148999A2 (fr) | Systeme d'echappement pour turbine a gaz | |
WO2003025350A1 (fr) | Dispositif de maintien des joints a lamelles d'etancheite | |
FR2897418A1 (fr) | Chambre de combustion annulaire d'une turbomachine | |
EP3736413B1 (fr) | Module de turbomachine équipé d'un dispositif de maintien de lamelles d' étanchéité | |
FR2825778A1 (fr) | Liaison coulissante entre un systeme d'injection d'une chambre de combustion et un fond de cette chambre de combustion | |
FR2896575A1 (fr) | Chambre de combustion annulaire d'une turbomachine | |
FR2825782A1 (fr) | Montage flottant radial de chambre de combustion cmc de turbomachine dans un carter metallique | |
FR3111964A1 (fr) | Assemblage d’une pièce de chambre de combustion par recouvrement par une autre pièce | |
FR3010774A1 (fr) | Turbomachine a chambre de combustion maintenue par une couronne de fixation metallique | |
FR3076860A1 (fr) | Bras de passage de servitudes pour turbomachine |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
17P | Request for examination filed |
Effective date: 20020610 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE TR |
|
AX | Request for extension of the european patent |
Free format text: AL;LT;LV;MK;RO;SI |
|
AKX | Designation fees paid |
Designated state(s): DE FR GB |
|
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: SNECMA |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): DE FR GB |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
REF | Corresponds to: |
Ref document number: 60229464 Country of ref document: DE Date of ref document: 20081204 Kind code of ref document: P |
|
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
26N | No opposition filed |
Effective date: 20090723 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 15 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 16 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: CD Owner name: SAFRAN AIRCRAFT ENGINES Effective date: 20170719 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 17 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20210519 Year of fee payment: 20 Ref country code: DE Payment date: 20210519 Year of fee payment: 20 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20210519 Year of fee payment: 20 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R071 Ref document number: 60229464 Country of ref document: DE |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: PE20 Expiry date: 20220603 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: GB Free format text: LAPSE BECAUSE OF EXPIRATION OF PROTECTION Effective date: 20220603 |