EP1265030A1 - Accrochage de chambre de combustion CMC de turbomachine par viroles de liaison souples - Google Patents
Accrochage de chambre de combustion CMC de turbomachine par viroles de liaison souples Download PDFInfo
- Publication number
- EP1265030A1 EP1265030A1 EP02291359A EP02291359A EP1265030A1 EP 1265030 A1 EP1265030 A1 EP 1265030A1 EP 02291359 A EP02291359 A EP 02291359A EP 02291359 A EP02291359 A EP 02291359A EP 1265030 A1 EP1265030 A1 EP 1265030A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- internal
- combustion chamber
- external
- sectored
- flexible
- 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
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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
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2230/00—Manufacture
- F05B2230/60—Assembly methods
- F05B2230/604—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins
- F05B2230/606—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins using maintaining alignment while permitting differential dilatation
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 metallic type materials.
- HPT nozzle inlet distributor
- the combustion chamber as well as the casing (also called envelope) of this chamber are made in metallic type materials.
- 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 sectored distributor of metallic material forming the stage input with fixed blades of a high pressure turbine, characterized in that said combustion chamber is held in position by a flexible sectored ferrule of metallic material of which a first end is fixed by first means for fixing to said combustion chamber and including a second end forming a flange is fixed to said envelope by second fixing means. Said first fixing means also ensure the connection of said chamber combustion with said sectored distributor.
- the first fixing means are constituted by a plurality of bolts.
- the flexible metallic segmented ferrule has holes ventilation to allow the passage of a coolant and a plurality of parallel sectoring slots ending at the most upstream of said ventilation openings.
- the sectoring slots are sized to compensate for the thermal expansion existing between the chamber of combustion in composite material and the envelope in metallic material.
- the turbomachine includes an envelope having external and internal annular walls in metallic material delimiting between them a space for successively receiving, in the direction F of gas flow, a fuel injection assembly, and on the one hand an annular combustion chamber of composite material formed an external axial wall, an internal axial wall and a transverse wall which constitutes the bottom of this combustion chamber, and on the other hand a sectored annular distributor of metallic material formed of a plurality fixed blades mounted between an external sectored circular platform and a internal sectored circular platform, downstream ends are provided said external and internal axial walls of the combustion chamber are held in position by flexible external and internal ferrules made of material metallic whose first ends are fixed to said downstream ends external and internal by first means of attachment and including seconds flange ends are attached to said outer annular casings and internal by second fixing means.
- these first fixing means comprise on the one hand first holding means for holding said downstream end portion of the internal axial wall of the combustion chamber between said platform internal sectored circular of the distributor and said first end of the shell flexible internal sectorized and secondly second holding means for maintain said downstream end portion of the external axial wall of the combustion between said circular sectored external platform of the distributor and said first end of the external sectored flexible ferrule.
- said first end of the flexible segmented ferrule internal has a downstream part forming a flange and serving as a support for a seal sealing said internal annular wall of the envelope.
- said internal annular wall of the envelope has a flange, a circular groove can receive a "omega” type circular seal designed to seal between this said flange of the internal annular wall of the envelope and said downstream part forming a flange.
- 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 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 24 high temperature composite material, 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 in particular to allow injection of the fuel and part of the oxidant in the combustion chamber 24, and finally an annular distributor 42 of metallic material forming a stage inlet of a high pressure turbine (not shown) and comprising conventionally
- the combustion chamber 26, 28 is maintained in position by a flexible ferrule made of metallic material 56, 60 of which a first end 56a, 56b is fixed to a downstream end 26a, 26b of the axial wall of the combustion chamber by first fixing means 50, 52 and a second flange end 56b, 60b is fixed to the casing 12, 14 by second fixing means 54, 58.
- This flexible ferrule is partly sectorized to compensate for expansion differences between the CMC chamber and the envelope metallic.
- the first fixing means 50, 52 also ensure the maintenance of the distributor 42 between the walls of the chamber 26, 28.
- the downstream end of the external axial wall 26a (respectively internal 28a) of the combustion is mounted between the external platform 46 (respectively internal 48) of the distributor and the first end of the flexible segmented external ferrule 60a (respectively internal 56a) of metallic material, the second end of which forming a flange 60b, 56b is fixed to the outer annular casing 12 (respectively internal 14), the assembly formed by these three elements, end downstream of the external (internal) axial wall, external (internal) platform of the distributor and first end of the external (internal) sectored flexible ferrule, being held tight by the first fastening means.
- first fixing means comprise, on the one hand, the first holding means 50 which hold the downstream end by pinching 28a of the internal axial wall 28 of the combustion chamber (opposite to the upstream end 38) between the internal sectored circular platform of the distributor 48 and the first end 56a of the sectored flexible ferrule internal metallic 56 and, secondly, second holding means 52 which hold the downstream end 26a of the axial wall by pinching external of the combustion chamber (opposite the upstream end 36) between the external sectorized circular platform of distributor 46 and the first end 60a of the external metalized flexible ferrule 60.
- the second fixing means comprise on the one hand first connecting means 54 for fixing the upstream flange 56b of the flexible ferrule segmented internal to the internal annular envelope 14 and on the other hand second connecting means 58 for fixing the upstream flange 60b of the sectored flexible ferrule external to the external annular envelope 12.
- the first 50 and second 52 holding means like the first 54 and second 58 connecting means are advantageously constituted by a plurality of bolts.
- the first end 56a of the internal flexible metallic ferrule 56 is advantageously provided with a downstream part 66 forming a flange serving as a support for a seal mounted in a flange 64 of this annular casing internal.
- Passage orifices 68, 70 formed in the metal platforms external 46 and internal 48 of the distributor 42 are further provided to ensure cooling of the stationary vanes 44 of the distributor at the inlet of the turbine rotor high pressure from the compressed oxidizer available at the outlet of the diffusion 18 and flowing in two streams F1, F2 on either side of the combustion 24.
- These cooling flows will first be passed between the different sectors of internal and external metallic segmented flexible ferrules and in addition by ventilation openings 56c, 60c formed in these ferrules at level of separation slots 72, 74 between sectors (see for example the figure 3).
- These sectoring slots are dimensionally determined to compensate for the thermal expansion existing between the combustion chamber by composite material and the envelope of metallic material.
- the flange 64 of the casing internal annular has a circular groove 76 for receiving a seal “omega” type 78 sealing circular intended to seal between this flange of the internal annular envelope and the downstream end forming flange 66 of the internal metallic ferrule 48.
- the platform external circular of the distributor 46 has a flange 80 provided with a groove circular 82 to receive a lamellar joint 84 one end of which will come in contact with the outer annular casing 12 to ensure tightness with respect. of the flow F1 which will then be forced to flow through the orifices 68 (also after having crossed the sectoring slots 74 and the ventilation openings 60c).
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Gasket Seals (AREA)
Abstract
Description
- la figure 1 est une vue 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, et
- la figure 3 montre en perspective détaillée la liaison turbine haute pression/chambre de combustion au niveau de la plate-forme externe du distributeur.
- 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 (11)
- 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 sectorisé en matériau métallique (42) formant l'étage d'entrée à aubes fixes (44) d'une turbine haute pression, caractérisée en ce que ladite chambre de combustion est maintenue en position par une virole souple sectorisée en matériau métallique (56, 60) dont une première extrémité (56a, 60a) est fixée par des premiers moyens de fixation (50, 52) à ladite chambre de combustion et dont une seconde extrémité formant bride (56b, 60b) est fixée à ladite enveloppe par des seconds moyens de fixation (54, 58).
- Turbomachine selon la revendication 1, caractérisée en ce que lesdits premiers moyens de fixation assurent en outre la liaison de ladite chambre de combustion avec ledit distributeur sectorisé.
- Turbomachine selon la revendication 1 ou la revendication 2, caractérisée en ce que lesdits premiers moyens de fixation sont constitués par une pluralité de boulons.
- Turbomachine selon la revendication 1, caractérisée en ce que ladite virole souple sectorisée métallique comporte des orifices de ventilation (56c, 60c) pour permettre le passage d'un fluide de refroidissement.
- Turbomachine selon la revendication 4, caractérisée en ce que ladite virole souple sectorisée métallique comporte une pluralité de fentes de sectorisation parallèles (72, 74) se terminant au niveau des plus amont desdits orifices de ventilation.
- Turbomachine selon la revendication 5, caractérisée en ce que lesdites fentes de sectorisation sont dimensionnées pour compenser la dilatation thermique existant entre la chambre de combustion en matériau composite et l'enveloppe en matériau métallique.
- Turbomachine comprenant une enveloppe ayant des parois annulaires externe (12) et interne (14) en matériau métallique délimitant entre elles un espace (16) pour recevoir successivement, dans le sens F d'écoulement des gaz, un ensemble d'injection d'un carburant (20, 22), et 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 circulaire sectorisée externe (46) et une plate-forme circulaire sectorisée interne (48), caractérisée en ce que des extrémités aval (26a, 28a) desdites parois axiales externe et interne de la chambre de combustion sont maintenues en position par des viroles souples sectorisées externe et interne en matériau métallique (56, 60) dont des premières extrémités (56a, 60a) sont fixées par des premiers moyens de fixation (50, 52) auxdites extrémités aval externe et interne et dont des secondes extrémités formant brides (56b, 60b) sont fixées auxdites enveloppes annulaires externe et interne par des seconds moyens de fixation (54, 58).
- Turbomachine selon la revendication 7, caractérisée en ce que lesdits premiers moyens de fixation comportent d'une part des premiers moyens de maintien (50) pour maintenir ladite extrémité aval de la paroi axiale interne de la chambre de combustion entre ladite plate-forme circulaire sectorisée interne du distributeur et ladite première extrémité de la virole souple sectorisée interne et d'autre part des seconds moyens de maintien (52) pour maintenir ladite extrémité aval de la paroi axiale externe de la chambre de combustion entre ladite plate-forme circulaire sectorisée externe du distributeur et ladite première extrémité de la virole souple sectorisée externe.
- Turbomachine selon la revendication 8, caractérisée en ce que lesdits premiers et seconds moyens de maintien sont constitués par une pluralité de boulons.
- Turbomachine selon la revendication 7, caractérisée en ce que ladite première extrémité de la virole souple sectorisée interne comporte une partie aval formant bride (66) et servant d'appui pour un joint d'étanchéité (78) de ladite paroi annulaire interne de l'enveloppe.
- Turbomachine selon la revendication 10, caractérisée en ce que ladite paroi annulaire interne de l'enveloppe comporte une bride (64) dont une rainure circulaire (76) reçoit 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 partie aval formant bride.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0107375 | 2001-06-06 | ||
FR0107375A FR2825787B1 (fr) | 2001-06-06 | 2001-06-06 | Montage de chambre de combustion cmc de turbomachine par viroles de liaison souples |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1265030A1 true EP1265030A1 (fr) | 2002-12-11 |
EP1265030B1 EP1265030B1 (fr) | 2008-07-09 |
Family
ID=8863996
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP02291359A Expired - Lifetime EP1265030B1 (fr) | 2001-06-06 | 2002-06-04 | Accrochage de chambre de combustion CMC de turbomachine par viroles de liaison souples |
Country Status (5)
Country | Link |
---|---|
US (1) | US6823676B2 (fr) |
EP (1) | EP1265030B1 (fr) |
JP (1) | JP3984101B2 (fr) |
DE (1) | DE60227455D1 (fr) |
FR (1) | FR2825787B1 (fr) |
Families Citing this family (32)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1312865A1 (fr) * | 2001-11-15 | 2003-05-21 | Siemens Aktiengesellschaft | Chambre de combustion annulaire de turbine à gaz |
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 |
US6931855B2 (en) | 2003-05-12 | 2005-08-23 | Siemens Westinghouse Power Corporation | Attachment system for coupling combustor liners to a carrier of a turbine combustor |
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 |
FR2860039B1 (fr) * | 2003-09-19 | 2005-11-25 | Snecma Moteurs | Realisation de l'etancheite dans un turboreacteur pour le prelevement cabine par joints double sens a lamelles |
US7338244B2 (en) * | 2004-01-13 | 2008-03-04 | Siemens Power Generation, Inc. | Attachment device for turbine combustor liner |
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 |
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 |
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 |
US7647779B2 (en) * | 2005-04-27 | 2010-01-19 | United Technologies Corporation | Compliant metal support for ceramic combustor liner in a gas turbine engine |
US7721547B2 (en) * | 2005-06-27 | 2010-05-25 | Siemens Energy, Inc. | Combustion transition duct providing stage 1 tangential turning for turbine engines |
US7805946B2 (en) * | 2005-12-08 | 2010-10-05 | Siemens Energy, Inc. | Combustor flow sleeve attachment system |
US8038389B2 (en) * | 2006-01-04 | 2011-10-18 | General Electric Company | Method and apparatus for assembling turbine nozzle assembly |
US7578134B2 (en) * | 2006-01-11 | 2009-08-25 | General Electric Company | Methods and apparatus for assembling gas turbine engines |
FR2913051B1 (fr) * | 2007-02-28 | 2011-06-10 | Snecma | Etage de turbine dans une turbomachine |
FR2920525B1 (fr) * | 2007-08-31 | 2014-06-13 | Snecma | Separateur pour alimentation de l'air de refroidissement d'une turbine |
JP5109719B2 (ja) * | 2008-02-29 | 2012-12-26 | 株式会社Ihi | ライナー支持構造 |
US8388307B2 (en) * | 2009-07-21 | 2013-03-05 | Honeywell International Inc. | Turbine nozzle assembly including radially-compliant spring member for gas turbine engine |
CN102128719B (zh) * | 2010-12-13 | 2012-10-24 | 中国航空动力机械研究所 | 扇形回流燃烧室及其对开式燃烧室机匣 |
US9335051B2 (en) * | 2011-07-13 | 2016-05-10 | United Technologies Corporation | Ceramic matrix composite combustor vane ring assembly |
US9267691B2 (en) * | 2012-01-03 | 2016-02-23 | General Electric Company | Quick disconnect combustion endcover |
US9651258B2 (en) | 2013-03-15 | 2017-05-16 | Rolls-Royce Corporation | Shell and tiled liner arrangement for a combustor |
JP6614407B2 (ja) * | 2015-06-10 | 2019-12-04 | 株式会社Ihi | タービン |
US10393381B2 (en) | 2017-01-27 | 2019-08-27 | General Electric Company | Unitary flow path structure |
US10371383B2 (en) * | 2017-01-27 | 2019-08-06 | 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 |
US10385776B2 (en) | 2017-02-23 | 2019-08-20 | General Electric Company | Methods for assembling a unitary flow path structure |
FR3081027B1 (fr) * | 2018-05-09 | 2020-10-02 | Safran Aircraft Engines | Turbomachine comportant un circuit de prelevement d'air |
CN111023154A (zh) * | 2019-12-31 | 2020-04-17 | 新奥能源动力科技(上海)有限公司 | 一种燃油喷嘴及燃烧室 |
US11428160B2 (en) | 2020-12-31 | 2022-08-30 | General Electric Company | Gas turbine engine with interdigitated turbine and gear assembly |
US11859819B2 (en) | 2021-10-15 | 2024-01-02 | General Electric Company | Ceramic composite combustor dome and liners |
CN115507392B (zh) * | 2022-09-16 | 2024-04-02 | 中国航发湖南动力机械研究所 | 一种陶瓷基复合材料火焰筒与金属件的连接结构 |
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GB1570875A (en) * | 1977-03-16 | 1980-07-09 | Lucas Industries Ltd | Combustion equipment |
DE3731901A1 (de) * | 1987-09-23 | 1989-04-13 | Mtu Muenchen Gmbh | Verbindung von keramischen und metallischen formteilen |
US4821522A (en) * | 1987-07-02 | 1989-04-18 | United Technologies Corporation | Sealing and cooling arrangement for combustor vane interface |
US5701733A (en) * | 1995-12-22 | 1997-12-30 | General Electric Company | Double rabbet combustor mount |
US6131384A (en) * | 1997-10-16 | 2000-10-17 | Rolls-Royce Deutschland Gmbh | Suspension device for annular gas turbine combustion chambers |
Family Cites Families (11)
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US2268464A (en) * | 1939-09-29 | 1941-12-30 | Bbc Brown Boveri & Cie | Combustion chamber |
FR962862A (fr) * | 1946-10-26 | 1950-06-22 | ||
US4688378A (en) * | 1983-12-12 | 1987-08-25 | United Technologies Corporation | One piece band seal |
US4739621A (en) * | 1984-10-11 | 1988-04-26 | United Technologies Corporation | Cooling scheme for combustor vane interface |
FR2686683B1 (fr) * | 1992-01-28 | 1994-04-01 | Snecma | Turbomachine a chambre de combustion demontable. |
US5363643A (en) * | 1993-02-08 | 1994-11-15 | General Electric Company | Segmented combustor |
US6182451B1 (en) * | 1994-09-14 | 2001-02-06 | Alliedsignal Inc. | Gas turbine combustor waving ceramic combustor cans and an annular metallic combustor |
US5813832A (en) * | 1996-12-05 | 1998-09-29 | General Electric Company | Turbine engine vane segment |
US5851679A (en) * | 1996-12-17 | 1998-12-22 | General Electric Company | Multilayer dielectric stack coated part for contact with combustion gases |
US6334298B1 (en) * | 2000-07-14 | 2002-01-01 | General Electric Company | Gas turbine combustor having dome-to-liner joint |
US6497104B1 (en) * | 2000-10-30 | 2002-12-24 | General Electric Company | Damped combustion cowl structure |
-
2001
- 2001-06-06 FR FR0107375A patent/FR2825787B1/fr not_active Expired - Fee Related
-
2002
- 2002-05-31 JP JP2002158746A patent/JP3984101B2/ja not_active Expired - Lifetime
- 2002-06-04 DE DE60227455T patent/DE60227455D1/de not_active Expired - Lifetime
- 2002-06-04 EP EP02291359A patent/EP1265030B1/fr not_active Expired - Lifetime
- 2002-06-05 US US10/161,805 patent/US6823676B2/en not_active Expired - Lifetime
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1570875A (en) * | 1977-03-16 | 1980-07-09 | Lucas Industries Ltd | Combustion equipment |
US4821522A (en) * | 1987-07-02 | 1989-04-18 | United Technologies Corporation | Sealing and cooling arrangement for combustor vane interface |
DE3731901A1 (de) * | 1987-09-23 | 1989-04-13 | Mtu Muenchen Gmbh | Verbindung von keramischen und metallischen formteilen |
US5701733A (en) * | 1995-12-22 | 1997-12-30 | General Electric Company | Double rabbet combustor mount |
US6131384A (en) * | 1997-10-16 | 2000-10-17 | Rolls-Royce Deutschland Gmbh | Suspension device for annular gas turbine combustion chambers |
Also Published As
Publication number | Publication date |
---|---|
JP3984101B2 (ja) | 2007-10-03 |
FR2825787A1 (fr) | 2002-12-13 |
DE60227455D1 (de) | 2008-08-21 |
EP1265030B1 (fr) | 2008-07-09 |
FR2825787B1 (fr) | 2004-08-27 |
JP2002372242A (ja) | 2002-12-26 |
US6823676B2 (en) | 2004-11-30 |
US20030000223A1 (en) | 2003-01-02 |
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