EP1265032A1 - Architecture de chambre de combustion de turbomachine en matériau à matrice céramique - Google Patents
Architecture de chambre de combustion de turbomachine en matériau à matrice céramique Download PDFInfo
- Publication number
- EP1265032A1 EP1265032A1 EP02291361A EP02291361A EP1265032A1 EP 1265032 A1 EP1265032 A1 EP 1265032A1 EP 02291361 A EP02291361 A EP 02291361A EP 02291361 A EP02291361 A EP 02291361A EP 1265032 A1 EP1265032 A1 EP 1265032A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- combustion chamber
- distributor
- internal
- external
- envelope
- 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
- F23R3/007—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
- 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
- F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
-
- 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
- F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
- F23M2900/00—Special features of, or arrangements for combustion chambers
- F23M2900/05002—Means for accommodate thermal expansion of the wall liner
Definitions
- the present invention relates to the field of turbomachinery and more in particular it concerns the interface between the high pressure turbine and the combustion chamber of turbojets fitted with a combustion chamber CMC (ceramic matrix composite).
- CMC ceramic matrix composite
- the high pressure turbine including its inlet distributor (HPT nozzle), the combustion chamber as well as the casing (also called envelope) of this chamber are made in a same material, usually metallic.
- HPT nozzle inlet distributor
- the combustion chamber as well as the casing (also called envelope) of this chamber are made in a same material, usually metallic.
- metallic materials and composite materials have very different coefficients of thermal expansion. This results in particularly acute interface problems at the level of the distributor, at the inlet of the high pressure turbine, and of connection with the casing of the bedroom.
- the present invention overcomes these drawbacks by proposing a connection housing-chamber having the capacity to absorb the displacements induced by differences in the expansion coefficients of these parts.
- An object of the invention is also to propose a structure of simple form and the manufacture of which is particularly easy.
- a turbomachine comprising, in a envelope of metallic material and in a direction F of gas flow, a fuel injection assembly, a material combustion chamber composite and a distributor of metallic material forming the input stage to fixed blades of a high pressure turbine, and said distributor being supported by said envelope and fixed thereto by first removable fixing means, characterized in that said combustion chamber is mounted floating in said envelope and held in position by the only said distributor to which it is fixed elastically by second removable fixing means.
- the first removable fixing means are suitable for allow free radial expansion of said dispenser relative to said envelope.
- said second means of removable fasteners comprise firstly first holding means for pinch hold an internal axial end wall of said chamber combustion between an internal circular distributor platform and a flange serving as a support for an internal annular wall of said envelope and of the second holding means for holding a wall with elastic preload axial external end of said combustion chamber on a platform external circular of the distributor.
- the support flange is sectorized to compensate for deviations circumferential geometries resulting from the differential expansion existing at high temperatures between said internal circular platform of the dispenser and said internal axial wall of the combustion chamber.
- This support flange is mounted between a flange of said inner annular wall of the envelope and a ferrule of metallic material held against this flange by said first removable fixing means.
- said first removable fixing means comprise a plurality of bolts, each of the screw axes which passes through a corresponding oblong hole of said support flange is provided with a shoulder on which is supported on said ferrule so as to allow sliding of said support flange between said ferrule and said flange of the internal annular wall of the envelope.
- said flange of the wall inner annular of the envelope has a circular groove for receiving a "omega" type circular seal designed to seal between this said flange of the internal annular wall of the envelope and said support flange.
- a ferrule of composite material advantageously brazed on said external end wall of the combustion chamber is maintained with a elastic prestress against said external circular platform of the distributor by the second holding means, said ferrule comprising a groove circular to receive an omega-type circular seal intended for sealing between said outer end wall of the combustion and said external circular platform of the distributor.
- this space 16 comprising, in the direction of flow of the gases, first of all an injection assembly formed by a plurality of injection systems 20 and regularly distributed around the duct 18 and each comprising a nozzle fuel injection 22 fixed to the outer annular casing 12 (in a to simplify the drawings, the mixer and the deflector associated with each injection nozzle have not been shown), then a combustion chamber in high temperature composite material 24, of CMC type or others (carbon by example), formed of an external axial wall 26 and an internal axial wall 28, both coaxial with axis 10, and a transverse wall 30 which constitutes the bottom of this combustion chamber and which has flaps 32, 34 fixed by all suitable means, for example metal or refractory head bolts conical), on upstream ends 36, 38 of the axial walls 26, 28, this bottom of the chamber 30 being provided with orifices 40 to allow the injection of fuel and of a part of the oxidizer in the combustion chamber 24, and finally a annular distributor 42 of metallic material forming an inlet stage of a high pressure turbine (not shown) and conventionally
- the combustion chamber is mounted floating in the annular casing and held in position by the only distributor to whom it is fixed elastically by second removable fixing means which on the one hand have first holding means 52 for holding by pinch an internal axial end wall 54 of the combustion chamber (opposite the upstream end 38) between the internal circular platform of the distributor 48 and a flange 56 serving to support the internal annular casing 14 and second holding means 58 for holding with a prestress elastic 60 an external axial end wall 62 of said chamber combustion (opposite the upstream end 36) on the external circular platform distributor 46.
- the support flange 56 is mounted between a flange 64 of the internal annular casing 14 and a ferrule made of metallic material 66 held against this flange by the first removable fixing means 50.
- Passage holes 68, 70 for the passage of compressed oxidizer previously separated, at the outlet of the diffusion duct 18, into at least two streams distinct F1, F2 flowing on either side of the combustion chamber 24 (and ensuring in particular its cooling), are provided in the platforms metallic 46 and internal 48 of the distributor 42 to ensure cooling of the stationary vanes 44 of the distributor at the inlet of the turbine rotor high pressure.
- the combustion chamber 24 having a coefficient of thermal expansion very different from the other metal parts forming the turbomachine, in particular the distributor 42 to which it is fixed and the annular casing 12, 14, it is provided that the first removable fixing means 50 are adapted to allow at high temperatures, a free radial expansion of the dispenser relative to the annular envelope.
- the support flange 56 is pierced with holes oblongs 72 intended to cooperate with the screw axes of the plurality of bolts 50 one shoulder 74 of which serves to support the ferrule 66 so as to allow sliding of this support flange between the ferrule and the flange 64 of the casing internal annular 14.
- this flange is sectorized to compensate for deviations circumferential geometries resulting from the differential expansion existing at these high temperatures between the internal circular platform 48 of the dispenser and the internal axial wall 28, 54 of the combustion chamber.
- the flange of the internal annular casing 64 comprises a circular groove 76 for receiving a type circular seal "Omega" 78 intended to seal between this flange of the envelope internal annular and the support flange 56.
- the external circular platform dispenser 46 has a flange 80 provided with a circular groove 82 for receive a lamellar seal 84 one end of which will come into contact with the outer annular casing 12 to seal against the flow F1.
- the seal between the combustion chamber 24 and the distributor 42 it is provided between the outer end wall of the combustion chamber 62 and the external circular platform of the distributor 46 also by means of a "Omega" type 86 seal mounted in a groove circular 88 of a ferrule made of composite material 90, advantageously brazed on the outer end wall of the combustion chamber 62, and held with elastic preload (obtained for example by spring 60) against the platform external circular of the distributor 46 by the second holding means 58.
Abstract
Description
- la figure 1 est une vue schématique en demi-coupe axiale d'une partie centrale d'une turbomachine,
- la figure 2 montre en perspective détaillée la liaison turbine haute pression - chambre de combustion au niveau de la plate-forme interne du distributeur,
- la figure 3 montre en perspective détaillée la liaison turbine haute pression - chambre de combustion au niveau de la plate-forme externe du distributeur, et
- la figure 4 est une vue selon IV de la figure 1.
- une enveloppe comportant une paroi annulaire externe (ou carter externe) 12 en matériau métallique, d'axe longitudinal 10, et une paroi annulaire interne (ou carter externe) coaxiale 14 également en matériau métallique,
- un espace annulaire 16 compris entre les deux parois annulaires 12, 14 de cette enveloppe 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 définissant un flux général F d'écoulement des gaz,
Claims (10)
- Turbomachine comportant, dans une enveloppe en matériau métallique (12, 14) et selon un sens F d'écoulement des gaz, un ensemble d'injection d'un carburant (20 ; 22), une chambre de combustion en matériau composite (24) et un distributeur en matériau métallique (42) formant l'étage d'entrée à aubes fixes (44) d'une turbine haute pression, et ledit distributeur étant supporté par ladite enveloppe et fixé à celle-ci par des premiers moyens de fixation amovibles (50), caractérisée en ce que ladite chambre de combustion est montée flottante dans ladite enveloppe et maintenue en position par le seul dit distributeur auquel elle est fixée de façon élastique par des seconds moyens de fixation amovibles (52, 58, 60).
- Turbomachine selon la revendication 1, caractérisée en ce que lesdits premiers moyens de fixation amovibles sont adaptés pour permettre une libre dilatation radiale dudit distributeur par rapport à ladite enveloppe.
- Turbomachine selon la revendication 1, caractérisée en ce que lesdits seconds moyens de fixation amovibles comportent d'une part des premiers moyens de maintien (52) pour maintenir par pincement une paroi axiale interne d'extrémité (54) de ladite chambre de combustion entre une plate-forme circulaire interne du distributeur (48) et une bride (56) servant de support à une paroi annulaire interne (14) de ladite enveloppe et des seconds moyens de maintien (58) pour maintenir avec une précontrainte élastique (60) une paroi axiale externe d'extrémité (62) de ladite chambre de combustion sur une plate-forme circulaire externe du distributeur (46).
- Turbomachine selon la revendication 3, caractérisée en ce que ladite bride support est sectorisée pour compenser les écarts géométriques circonférenciels résultant de la dilatation différentielle existant aux températures élevées entre ladite plate-forme circulaire interne du distributeur et ladite paroi axiale interne de la chambre de combustion.
- Turbomachine selon la revendication 3, caractérisée en ce que ladite bride support est montée entre une bride (64) de ladite paroi annulaire interne de l'enveloppe et une virole en matériau métallique (66) maintenue contre cette bride par lesdits premiers moyens de fixation amovibles.
- Turbomachine selon la revendication 5, caractérisée en ce que lesdits premiers moyens de fixation amovibles comportent une pluralité de boulons (50) dont chacun des axes de vis qui traverse un trou oblong correspondant (72) de ladite bride support est muni d'un épaulement (74) sur lequel est mis en appui ladite virole de façon à permettre un coulissement de ladite bride support entre ladite virole et ladite bride de la paroi annulaire interne de l'enveloppe.
- Turbomachine selon la revendication 6, caractérisée en ce que ladite bride de la paroi annulaire interne de l'enveloppe comporte une rainure circulaire (76) pour recevoir un joint circulaire d'étanchéité de type « oméga » (78) destiné à assurer l'étanchéité entre cette dite bride de la paroi annulaire interne de l'enveloppe et ladite bride support.
- Turbomachine selon la revendication 3, caractérisée en ce qu'elle comporte en outre une virole en matériau composite (90) avantageusement brasée sur ladite paroi externe d'extrémité de la chambre de combustion et maintenue avec une précontrainte élastique (60) contre ladite plate-forme circulaire externe du distributeur par lesdits seconds moyens de maintien.
- Turbomachine selon la revendication 8, caractérisée en ce que ladite virole comporte une rainure circulaire (88) pour recevoir un joint circulaire d'étanchéité de type « oméga » (86) destiné à assurer l'étanchéité entre ladite paroi externe d'extrémité de la chambre de combustion et ladite plate-forme circulaire externe du distributeur.
- Turbomachine comprenant une enveloppe annulaire externe (12) et une enveloppe annulaire interne (14) délimitant entre elles un espace (16) pour recevoir successivement, dans le sens F d'écoulement des gaz, d'une part une chambre de combustion annulaire (24) en matériau composite formée d'une paroi axiale externe (26), d'une paroi axiale interne (28) et d'une paroi transversale (30) qui constitue le fond de cette chambre de combustion, et d'autre part un distributeur annulaire sectorisé (42) en matériau métallique formé d'une pluralité d'aubes fixes (44) montées entre une plate-forme axiale externe (46) et une plate-forme axiale interne (48), caractérisée en ce que les parties d'extrémité libres (54, 62) desdites parois axiales externe et interne de la chambre de combustion sont reliées auxdites plates-formes externe et interne du distributeur, ladite paroi axiale interne d'extrémité (54) de la chambre étant pincée au moyen de premiers moyens de maintien (52) entre ladite plate-forme interne du distributeur et une bride (56) servant de support à ladite enveloppe annulaire interne, et ladite paroi axiale externe d'extrémité (62) de la chambre étant maintenue avec une précontrainte élastique (60) contre ladite plate-forme externe du distributeur par des seconds moyens de maintien (58).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0107360A FR2825780B1 (fr) | 2001-06-06 | 2001-06-06 | Architecure de chambre de combustion de turbomachine en materiau a matrice ceramique |
FR0107360 | 2001-06-06 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1265032A1 true EP1265032A1 (fr) | 2002-12-11 |
EP1265032B1 EP1265032B1 (fr) | 2004-10-06 |
Family
ID=8863984
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP02291361A Expired - Lifetime EP1265032B1 (fr) | 2001-06-06 | 2002-06-04 | Architecture de chambre de combustion de turbomachine en matériau à matrice céramique |
Country Status (5)
Country | Link |
---|---|
US (1) | US6679062B2 (fr) |
EP (1) | EP1265032B1 (fr) |
JP (1) | JP3983603B2 (fr) |
DE (1) | DE60201467T2 (fr) |
FR (1) | FR2825780B1 (fr) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1431664A3 (fr) * | 2002-12-20 | 2006-01-18 | General Electric Company | Assemblage pour le montage de l'extrémité arrière d'une chemise en composite à matrice céramique à l'intérieur d'une chambre de combustion de turbine à gaz |
EP1795712A3 (fr) * | 2005-12-08 | 2008-03-05 | General Electric Company | Procédé et dispositif pour l'assemblage d'un moteur à turbine. |
EP1903283A1 (fr) * | 2006-09-22 | 2008-03-26 | Snecma | Chambre de combustion annulaire d'une turbomachine |
EP1719949A3 (fr) * | 2005-04-27 | 2009-09-02 | United Technologies Corporation | Support métallique d'une chemise de chambre de combustion en céramique de turbine à gaz |
Families Citing this family (23)
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 |
US7152411B2 (en) * | 2003-06-27 | 2006-12-26 | General Electric Company | Rabbet mounted combuster |
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 |
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 |
FR2871844B1 (fr) | 2004-06-17 | 2006-09-29 | Snecma Moteurs Sa | Montage etanche d'un distributeur de turbine haute pression sur une extremite d'une chambre de combustion dans une turbine a gaz |
FR2871845B1 (fr) * | 2004-06-17 | 2009-06-26 | Snecma Moteurs Sa | Montage de chambre de combustion de turbine a gaz avec distributeur integre de turbine haute pression |
US8038389B2 (en) * | 2006-01-04 | 2011-10-18 | General Electric Company | Method and apparatus for assembling turbine nozzle assembly |
EP1843009A1 (fr) | 2006-04-06 | 2007-10-10 | Siemens Aktiengesellschaft | Segment d'ailette de guidage d'une turbomachine, procédé de fabrication associé et turbomachine |
DE102006060857B4 (de) | 2006-12-22 | 2014-02-13 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | CMC-Brennkammerauskleidung in Doppelschichtbauweise |
EP1985806A1 (fr) * | 2007-04-27 | 2008-10-29 | Siemens Aktiengesellschaft | Refroidissement d'anneau de renforcement d'une aube fixe de turbine |
US8745989B2 (en) * | 2009-04-09 | 2014-06-10 | Pratt & Whitney Canada Corp. | Reverse flow ceramic matrix composite combustor |
US8226361B2 (en) * | 2009-07-08 | 2012-07-24 | General Electric Company | Composite article and support frame assembly |
US8206096B2 (en) * | 2009-07-08 | 2012-06-26 | General Electric Company | Composite turbine nozzle |
US9234431B2 (en) * | 2010-07-20 | 2016-01-12 | Siemens Energy, Inc. | Seal assembly for controlling fluid flow |
FR2963061B1 (fr) * | 2010-07-26 | 2012-07-27 | Snecma | Systeme d?injection de carburant pour turbo-reacteur et procede d?assemblage d?un tel systeme d?injection |
US9290261B2 (en) | 2011-06-09 | 2016-03-22 | United Technologies Corporation | Method and assembly for attaching components |
US10059431B2 (en) | 2011-06-09 | 2018-08-28 | United Technologies Corporation | Method and apparatus for attaching components having dissimilar rates of thermal expansion |
US9335051B2 (en) * | 2011-07-13 | 2016-05-10 | United Technologies Corporation | Ceramic matrix composite combustor vane ring assembly |
EP2971583B1 (fr) | 2013-03-15 | 2016-11-30 | Rolls-Royce North American Technologies, Inc. | Joints d'étanchéité pour turbine à gaz |
GB201315871D0 (en) * | 2013-09-06 | 2013-10-23 | Rolls Royce Plc | A combustion chamber arrangement |
US10816212B2 (en) * | 2016-04-22 | 2020-10-27 | Rolls-Royce Plc | Combustion chamber having a hook and groove connection |
US10495001B2 (en) | 2017-06-15 | 2019-12-03 | General Electric Company | Combustion section heat transfer system for a propulsion system |
US11708765B1 (en) | 2022-05-13 | 2023-07-25 | Raytheon Technologies Corporation | Gas turbine engine article with branched flange |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3965066A (en) * | 1974-03-15 | 1976-06-22 | General Electric Company | Combustor-turbine nozzle interconnection |
US5291732A (en) * | 1993-02-08 | 1994-03-08 | General Electric Company | Combustor liner support assembly |
EP1152191A2 (fr) * | 2000-05-05 | 2001-11-07 | General Electric Company | Chambre de combustion ayant une chemise de chambre de combustion faite de matériau composite à matrice céramique |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
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US3775975A (en) * | 1972-09-05 | 1973-12-04 | Gen Electric | Fuel distribution system |
US4912922A (en) * | 1972-12-19 | 1990-04-03 | General Electric Company | Combustion chamber construction |
US5335502A (en) * | 1992-09-09 | 1994-08-09 | General Electric Company | Arched combustor |
-
2001
- 2001-06-06 FR FR0107360A patent/FR2825780B1/fr not_active Expired - Fee Related
-
2002
- 2002-05-30 JP JP2002156754A patent/JP3983603B2/ja not_active Expired - Lifetime
- 2002-06-04 DE DE60201467T patent/DE60201467T2/de not_active Expired - Lifetime
- 2002-06-04 EP EP02291361A patent/EP1265032B1/fr not_active Expired - Lifetime
- 2002-06-05 US US10/162,384 patent/US6679062B2/en not_active Expired - Lifetime
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3965066A (en) * | 1974-03-15 | 1976-06-22 | General Electric Company | Combustor-turbine nozzle interconnection |
US5291732A (en) * | 1993-02-08 | 1994-03-08 | General Electric Company | Combustor liner support assembly |
EP1152191A2 (fr) * | 2000-05-05 | 2001-11-07 | General Electric Company | Chambre de combustion ayant une chemise de chambre de combustion faite de matériau composite à matrice céramique |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1431664A3 (fr) * | 2002-12-20 | 2006-01-18 | General Electric Company | Assemblage pour le montage de l'extrémité arrière d'une chemise en composite à matrice céramique à l'intérieur d'une chambre de combustion de turbine à gaz |
EP1719949A3 (fr) * | 2005-04-27 | 2009-09-02 | United Technologies Corporation | Support métallique d'une chemise de chambre de combustion en céramique de turbine à gaz |
US8122727B2 (en) | 2005-04-27 | 2012-02-28 | United Technologies Corporation | Compliant metal support for ceramic combustor liner in a gas turbine engine |
EP1795712A3 (fr) * | 2005-12-08 | 2008-03-05 | General Electric Company | Procédé et dispositif pour l'assemblage d'un moteur à turbine. |
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 |
---|---|
JP3983603B2 (ja) | 2007-09-26 |
EP1265032B1 (fr) | 2004-10-06 |
FR2825780A1 (fr) | 2002-12-13 |
DE60201467T2 (de) | 2006-03-09 |
US6679062B2 (en) | 2004-01-20 |
US20020184891A1 (en) | 2002-12-12 |
JP2003035104A (ja) | 2003-02-07 |
FR2825780B1 (fr) | 2003-08-29 |
DE60201467D1 (de) | 2004-11-11 |
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