EP1265030B1 - Mounting of a ceramic matrix composite combustion chamber with flexible shrouds - Google Patents
Mounting of a ceramic matrix composite combustion chamber with flexible shrouds Download PDFInfo
- Publication number
- EP1265030B1 EP1265030B1 EP02291359A EP02291359A EP1265030B1 EP 1265030 B1 EP1265030 B1 EP 1265030B1 EP 02291359 A EP02291359 A EP 02291359A EP 02291359 A EP02291359 A EP 02291359A EP 1265030 B1 EP1265030 B1 EP 1265030B1
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- EP
- European Patent Office
- Prior art keywords
- sectorized
- combustion chamber
- turbomachine
- flange
- shell
- 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.)
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Classifications
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- 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
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- 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 turbomachines and more particularly it relates to the interface between the high pressure turbine and the combustion chamber of turbojet engines provided with a combustion chamber made of CMC (ceramic matrix composite).
- CMC ceramic matrix composite
- the high pressure turbine including its inlet nozzle (HPT nozzle), the combustion chamber and the housing (also called envelope) of this chamber are made of metal type materials.
- HPT nozzle inlet nozzle
- the combustion chamber and the housing (also called envelope) of this chamber are made of metal type materials.
- the use of a metal chamber is from a thermal point of view totally inadequate and it must be resorted to a chamber based on CMC type high temperature composite materials.
- metallic materials However, metal materials and composite materials have very different coefficients of thermal expansion. This results, from an aerodynamic point of view, particularly acute interface problems at the distributor, inlet of the high pressure turbine, and connection with the housing of the chamber.
- US-A-5,851,679 shows a turbomachine with a chamber of CMC type material.
- the present invention overcomes these disadvantages by proposing a crankcase-chamber connection having the capacity to absorb the displacements induced by the differences of the expansion coefficients of these parts.
- An object of the invention is also to provide a structure of simple shape and whose manufacture is particularly easy.
- a turbomachine comprising, in an envelope of metallic material and in a direction F of gas flow, a fuel injection assembly, a composite material combustion chamber and a sectorized metal material distributor forming the fixed blade inlet stage of a high pressure turbine, characterized in that said combustion chamber is maintained in position by a sectorized flexible ferrule made of metallic material, a first end of which is fixed by first fastening means to said combustion chamber and a second flange end of which is fixed to said envelope by second fixing means. Said first fastening means further ensure the connection of said combustion chamber with said sectorized distributor.
- connection By this direct connection (integration) of the combustion chamber to the distributor, it avoids any misalignment of the gas stream in operation (thus ensuring a better supply of the high pressure turbine) while improving the sealing chamber-distributor.
- the connection to the envelope by a sectorized flexible hoop system further provides an appreciable weight gain for the combustion chamber compared to traditional rigid heavy-duty connection devices.
- the first fixing means consist of a plurality of bolts.
- the metallic split flexible ferrule comprises ventilation orifices to allow the passage of a cooling fluid and a plurality of parallel sectoring slots ending at the upstream of said ventilation orifices.
- the sectoring slots are dimensioned to compensate for the thermal expansion existing between the combustion chamber of composite material and the envelope of metallic material.
- the turbomachine comprises an envelope having outer and inner annular walls of metallic material delimiting between them a space for successively receiving, in the flow direction F of the gases, an injection assembly of a fuel, and on the one hand an annular combustion chamber of composite material formed of an outer axial wall, an inner axial wall and a transverse wall which constitutes the bottom of this combustion chamber, and secondly a segmented annular distributor made of metallic material formed of a plurality of fixed vanes mounted between an external sectorized circular platform and a internal sectorized circular platform, it is expected that downstream ends of said outer and inner axial walls of the combustion chamber are held in position by flexible outer and inner shells of metal material whose first ends are fixed to said external downstream ends and internally by first fixing means and second ends forming flanges are attached to said outer and inner annular envelopes by second fastening 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 internal sectorized circular platform of the distributor and said first end of the inner sectorized flexible ferrule and secondly second holding means for holding said end downstream portion of the outer axial wall of the combustion chamber between said outer sectorized circular platform of the distributor and said first end of the ferrule external sectorised flexible.
- said first end of the inner sectorized flexible ferrule comprises a downstream part forming a flange and serving as a support for a seal of said inner annular wall of the envelope.
- said inner annular wall of the casing comprises a flange of which a circular groove may receive an omega-type circular seal intended to seal said wall flange.
- annular inner envelope and said downstream portion forming a flange.
- this space 16 comprising, in the gas flow direction, firstly an injection assembly formed of a plurality of injection systems 20 regularly distributed around the conduit 18 and each having a fuel injection nozzle 22 fixed on the outer annular envelope 12 (for the sake of simplification of the drawings the mixer and the deflector associated with each injection nozzle have not been shown), then a combustion chamber 24 made of high temperature composite material, type CMC or others (carbon for example), formed of an outer axial wall 26 and an inner axial wall 28, both coaxial axis 10, and a transverse wall 30 which constitutes the bottom of this chamber of combustion and which comprises flaps 32, 34 fixed by any suitable means, for example metal bolts or refractory screws conical head, on upstream ends 36, 38 of the axial walls 26, 28, the bottom of the chamber 30 being po urvu orifices 40 to allow the injection of the fuel and a part of the oxidant in the combustion chamber 24, and finally an annular distributor 42 of metal material forming an inlet stage of a high pressure turbine (not shown) and conventionally comprising
- the combustion chamber 26, 28 is held in position by a flexible shell of metal material 56, 60, a first end 56a, 56b is fixed to a downstream end 26a, 26b of the axial wall of the chamber of combustion by first fixing means 50, 52 and a second end flange 56b, 60b is fixed to the casing 12, 14 by second fastening means 54, 58.
- This flexible ferrule is partially sectorized to compensate for the differences in dilation between the CMC chamber and the metal shell.
- the first attachment means 50, 52 also ensure the maintenance of the distributor 42 between the walls of the chamber 26, 28.
- the downstream end of the outer axial wall 26a (respectively internal 28a) of the combustion chamber is mounted between the external platform 46 (respectively internal 48) of the distributor and the first end of the external sectorized flexible shell 60a (respectively internal 56a) of metal material whose second flange end 60b, 56b is fixed to the outer annular envelope 12 (respectively internal 14), the assembly formed of these three elements, the downstream end of the external (internal) axial wall, the external (internal) distributor platform and the first end of the outer (internal) reinforced sectorised flexible shell, being maintained tightened by the first fastening means.
- first fixing means comprise, on the one hand, first holding means 50 which hold the downstream end 28a of the internal axial wall 28 of the combustion chamber (opposite to the upstream end 38) in a pinch position between the internal sectorized circular platform of the distributor 48 and the first end 56a of the internal metal sectorized flexible ring 56 and secondly second holding means 52 which hold the downstream end 26a of the wall by pinching axial axis of the combustion chamber (opposite to the upstream end 36) between the external sectorized circular platform of the distributor 46 and the first end 60a of the external metalized sectorized flexible ring 60.
- the second attachment means comprise firstly connecting means 54 for fixing the upstream flange 56b of the inner sectorized flexible ferrule to the inner annular envelope 14 and secondly second connecting means 58 for attaching the upstream flange 60b of the outer sectorized flexible ferrule to the outer annular envelope 12.
- the first 50 and second 52 holding means as the first 54 and second 58 connecting means are advantageously constituted by a plurality of bolts.
- the first end 56a of the inner metal flexible 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 inner annular envelope.
- Through-holes 68, 70 formed in the external metal 46 and inner metal platforms 48 of the distributor 42 are further provided to ensure cooling of the fixed vanes 44 of the inlet distributor of the rotor of the high-pressure turbine from the compressed oxidant available at the outlet of the diffusion duct 18 and flowing in two streams F1, F2 on either side of the combustion chamber 24. These cooling flows will be previously passed between the different sectors of the inner metalized and metalized flexible rings. external and further by ventilation holes 56c, 60c formed in these ferrules at separation slots 72, 74 between sectors (see for example the figure 3 ). These sectoring slots are dimensioned in a determined manner to compensate for the thermal expansion existing between the combustion chamber made of composite material and the envelope made of metallic material.
- the flange 64 of the inner annular casing has a circular groove 76 to receive a circular seal of "omega" type sealing 78 intended to ensure the seal between this flange of the inner annular envelope and the downstream flange end 66 of the inner metal ferrule 48.
- the flow of oxidant compressed in from the compressor and surrounding the chamber by F2 can reach the turbine only through the orifices 70 (after passing through the sectoring slots 72 and ventilation holes 56c).
- the external circular platform of the distributor 46 comprises a flange 80 provided with a circular groove 82 for receiving a blade seal 84, one end of which will come into contact with the outer annular envelope 12 to ensure a tightness screw. flow F1 which will then be forced to flow through the orifices 68 (also after passing through the sectoring slots 74 and the ventilation holes 60c).
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- 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)
Description
La présente invention se rapporte au domaine des turbomachines et plus particulièrement elle concerne l'interface entre la turbine haute pression et la chambre de combustion de turboréacteurs munis d'une chambre de combustion en CMC (composite à matrice céramique).The present invention relates to the field of turbomachines and more particularly it relates to the interface between the high pressure turbine and the combustion chamber of turbojet engines provided with a combustion chamber made of CMC (ceramic matrix composite).
Classiquement, dans une turbomachine, la turbine haute pression, notamment son distributeur d'entrée (HPT nozzle), la chambre de combustion ainsi que le carter (dit aussi enveloppe) de cette chambre sont réalisés dans des matériaux de type métallique. Cependant, dans certaines conditions particulières d'utilisation mettant en oeuvre des températures de combustion notablement élevées, l'emploi d'une chambre métallique s'avère d'un point de vue thermique totalement inadaptée et il doit être recouru à une chambre à base de matériaux composites haute température de type CMC. Toutefois, les difficultés de mise en oeuvre et le coût de ces matériaux font que leur utilisation est le plus souvent limitée à la chambre de combustion elle même, le distributeur d'entrée de la turbine haute pression et le carter restant alors réalisés plus classiquement en des matériaux métalliques. Or, les matériaux métalliques et les matériaux composites ont des coefficients de dilatation thermique très différents. Il en résulte, d'un point de vue aérodynamique, des problèmes particulièrement aigus d'interface au niveau du distributeur, en entrée de la turbine haute pression, et de liaison avec le carter de la chambre.
La présente invention pallie ces inconvénients en proposant une liaison carter-chambre ayant la capacité d'absorber les déplacements induits par les différences des coefficients de dilatation de ces pièces. Un but de l'invention est aussi de proposer une structure de forme simple et dont la fabrication soit particulièrement aisée.The present invention overcomes these disadvantages by proposing a crankcase-chamber connection having the capacity to absorb the displacements induced by the differences of the expansion coefficients of these parts. An object of the invention is also to provide a structure of simple shape and whose manufacture is particularly easy.
Ces buts sont atteints par une turbomachine comportant, dans une enveloppe en matériau métallique et selon un sens F d'écoulement des gaz, un ensemble d'injection d'un carburant, une chambre de combustion en matériau composite et un distributeur sectorisé en matériau métallique formant l'étage d'entrée à aubes fixes 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 dont une première extrémité est fixée par des premiers moyens de fixation à ladite chambre de combustion et dont une seconde extrémité formant bride est fixée à ladite enveloppe par des seconds moyens de fixation. Lesdits premiers moyens de fixation assurent en outre la liaison de ladite chambre de combustion avec ledit distributeur sectorisé.These objects are achieved by a turbomachine comprising, in an envelope of metallic material and in a direction F of gas flow, a fuel injection assembly, a composite material combustion chamber and a sectorized metal material distributor forming the fixed blade inlet stage of a high pressure turbine, characterized in that said combustion chamber is maintained in position by a sectorized flexible ferrule made of metallic material, a first end of which is fixed by first fastening means to said combustion chamber and a second flange end of which is fixed to said envelope by second fixing means. Said first fastening means further ensure the connection of said combustion chamber with said sectorized distributor.
Par ce rattachement direct (intégration) de la chambre de combustion au distributeur, on évite tout désalignement de la veine de gaz en fonctionnement (garantissant ainsi une meilleure alimentation de la turbine haute pression) tout en améliorant l'étanchéité chambre-distributeur. La liaison à l'enveloppe par un système de viroles souples sectorisées procure de plus un gain de masse appréciable pour la chambre de combustion par rapport aux dispositifs de liaison traditionnels à lourdes brides rigides.By this direct connection (integration) of the combustion chamber to the distributor, it avoids any misalignment of the gas stream in operation (thus ensuring a better supply of the high pressure turbine) while improving the sealing chamber-distributor. The connection to the envelope by a sectorized flexible hoop system further provides an appreciable weight gain for the combustion chamber compared to traditional rigid heavy-duty connection devices.
De préférence, les premiers moyens de fixation sont constitués par une pluralité de boulons. La virole souple sectorisée métallique comporte des orifices de ventilation pour permettre le passage d'un fluide de refroidissement et une pluralité de fentes de sectorisation parallèles se terminant au niveau des plus amont desdits orifices de ventilation. Les 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.Preferably, the first fixing means consist of a plurality of bolts. The metallic split flexible ferrule comprises ventilation orifices to allow the passage of a cooling fluid and a plurality of parallel sectoring slots ending at the upstream of said ventilation orifices. The sectoring slots are dimensioned to compensate for the thermal expansion existing between the combustion chamber of composite material and the envelope of metallic material.
Selon un mode de réalisation préférentiel dans lequel la turbomachine comprend une enveloppe ayant des parois annulaires externe et interne en matériau métallique délimitant entre elles un espace pour recevoir successivement, dans le sens F d'écoulement des gaz, un ensemble d'injection d'un carburant, et d'une part une chambre de combustion annulaire en matériau composite formée d'une paroi axiale externe, d'une paroi axiale interne et d'une paroi transversale qui constitue le fond de cette chambre de combustion, et d'autre part un distributeur annulaire sectorisé en matériau métallique formé d'une pluralité d'aubes fixes montées entre une plate-forme circulaire sectorisée externe et une plate-forme circulaire sectorisée interne, il est prévu que des extrémités aval desdites parois axiales externe et interne de la chambre de combustion sont maintenues en position par des viroles souples externe et interne en matériau métallique dont des premières extrémités sont fixées auxdites extrémités aval externe et interne par des premiers moyens de fixation et dont des secondes extrémités formant brides sont fixées auxdites enveloppes annulaires externe et interne par des seconds moyens de fixation.According to a preferred embodiment in which the turbomachine comprises an envelope having outer and inner annular walls of metallic material delimiting between them a space for successively receiving, in the flow direction F of the gases, an injection assembly of a fuel, and on the one hand an annular combustion chamber of composite material formed of an outer axial wall, an inner axial wall and a transverse wall which constitutes the bottom of this combustion chamber, and secondly a segmented annular distributor made of metallic material formed of a plurality of fixed vanes mounted between an external sectorized circular platform and a internal sectorized circular platform, it is expected that downstream ends of said outer and inner axial walls of the combustion chamber are held in position by flexible outer and inner shells of metal material whose first ends are fixed to said external downstream ends and internally by first fixing means and second ends forming flanges are attached to said outer and inner annular envelopes by second fastening means.
Avantageusement, ces premiers moyens de fixation comportent d'une part des premiers moyens de maintien pour maintenir ladite partie aval d'extrémité 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 pour maintenir ladite partie aval d'extrémité 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.Advantageously, 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 internal sectorized circular platform of the distributor and said first end of the inner sectorized flexible ferrule and secondly second holding means for holding said end downstream portion of the outer axial wall of the combustion chamber between said outer sectorized circular platform of the distributor and said first end of the ferrule external sectorised flexible.
De préférence, ladite première extrémité de la virole souple sectorisée interne comporte une partie aval formant bride et servant d'appui pour un joint d'étanchéité de ladite paroi annulaire interne de l'enveloppe.Preferably, said first end of the inner sectorized flexible ferrule comprises a downstream part forming a flange and serving as a support for a seal of said inner annular wall of the envelope.
Pour assurer l'étanchéité de la turbomachine, ladite paroi annulaire interne de l'enveloppe comporte une bride dont une rainure circulaire peut recevoir un joint circulaire d'étanchéité de type « oméga » destiné à assurer l'étanchéité entre cette dite bride de la paroi annulaire interne de l'enveloppe et ladite partie aval formant bride.To ensure the tightness of the turbomachine, said inner annular wall of the casing comprises a flange of which a circular groove may receive an omega-type circular seal intended to seal said wall flange. annular inner envelope and said downstream portion forming a flange.
Les caractéristiques et avantages de la présente invention ressortiront mieux de la description suivante, faite à titre indicatif et non limitatif, en regard des dessins annexés sur lesquels :
- 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.
- the
figure 1 is a schematic axial half-sectional view of a central part of a turbomachine, - the
figure 2 detailed perspective view of the high-pressure turbine / combustion chamber connection at the level of the internal platform of the distributor, and - the
figure 3 detailed perspective view of the high-pressure turbine / combustion chamber connection at the distributor's external platform.
La
- . 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,
- . an envelope comprising an outer annular wall (or outer casing) 12 of metal material, of
longitudinal axis 10, and an inner annular wall (or outer casing) coaxial 14 also made of metallic material, - . an
annular space 16 between the two 12, 14 of this envelope receiving the compressed oxidant, generally air, coming upstream of a compressor (not shown) of the turbomachine, through an annular duct ofannular walls diffusion 18 defining a general flow F of gas flow,
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 le mélangeur et le déflecteur associés à chaque buse d'injection n'ont pas été représentés), ensuite une chambre de combustion 24 en matériau composite haute température, de type CMC ou autres (carbone par exemple), formée d'une paroi axiale externe 26 et d'une paroi axiale interne 28, toutes deux coaxiales d'axe 10, et d'une paroi transversale 30 qui constitue le fond de cette chambre de combustion et qui comporte des rabats 32, 34 fixés par tous moyens adaptés, par exemple des boulons métalliques ou réfractaires à vis à tête conique, sur des extrémités amont 36, 38 des parois axiales 26, 28, ce fond de la chambre 30 étant pourvu d'orifices 40 pour notamment permettre l'injection du carburant et d'une partie du comburant dans la chambre de combustion 24, et enfin un distributeur annulaire 42 en matériau métallique formant un étage d'entrée d'une turbine haute pression (non représentée) et comportant classiquement une pluralité d'aubes fixes 44 montées entre une plate-forme circulaire sectorisée externe 46 et une plate-forme circulaire sectorisée interne 48.this
Selon l'invention, la chambre de combustion 26, 28 est maintenue en position par une virole souple en matériau métallique 56, 60 dont une première extrémité 56a, 56b est fixée à une extrémité aval 26a, 26b de la paroi axiale de la chambre de combustion par des premiers moyens de fixation 50, 52 et une seconde extrémité formant bride 56b, 60b est fixée à l'enveloppe 12, 14 par des seconds moyens de fixation 54, 58. Cette virole souple est en partie sectorisée pour compenser les écarts de dilatation entre la chambre en CMC et l'enveloppe métallique. Les premiers moyens de fixation 50, 52 assurent aussi le maintien du distributeur 42 entre les parois de la chambre 26, 28. Ainsi, l'extrémité aval de la paroi axiale externe 26a (respectivement interne 28a ) de la chambre de combustion est montée entre la plate-forme externe 46 (respectivement interne 48) du distributeur et la première extrémité de la virole souple sectorisée externe 60a (respectivement interne 56a) en matériau métallique dont la seconde extrémité formant bride 60b, 56b est fixée à l'enveloppe annulaire externe 12 (respectivement interne 14), l'ensemble formé de ces trois éléments, extrémité aval de la paroi axiale externe (interne), plate-forme externe (interne) du distributeur et première extrémité de la virole souple sectorisée externe (interne), étant maintenu serré par les premiers moyens de fixation.According to the invention, the
Ces premiers moyens de fixation comportent, d'une part des premiers moyens de maintien 50 qui assurent le maintien par pincement de l'extrémité aval 28a de la paroi axiale interne 28 de la chambre de combustion (opposée à l'extrémité amont 38) entre la plate-forme circulaire sectorisée interne du distributeur 48 et la première extrémité 56a de la virole souple sectorisée métallique interne 56 et, d'autre part des seconds moyens de maintien 52 qui assurent le maintien par pincement de l'extrémité aval 26a de la paroi axiale externe de la chambre de combustion (opposée à l'extrémité amont 36) entre la plate-forme circulaire sectorisée externe du distributeur 46 et la première extrémité 60a de la virole souple sectorisée métallique externe 60.These first fixing means comprise, on the one hand,
De même, les seconds moyens de fixation comportent d'une part des premiers moyens de liaison 54 pour fixer la bride amont 56b de la virole souple sectorisée interne à l'enveloppe annulaire interne 14 et d'autre part des second moyens de liaison 58 pour fixer la bride amont 60b de la virole souple sectorisée externe à l'enveloppe annulaire externe 12.Similarly, the second attachment means comprise firstly connecting means 54 for fixing the
Les premiers 50 et seconds 52 moyens de maintien comme les premiers 54 et seconds 58 moyens de liaison sont avantageusement constitués par une pluralité de boulons.The first 50 and second 52 holding means as the first 54 and second 58 connecting means are advantageously constituted by a plurality of bolts.
La première extrémité 56a de la virole souple métallique interne 56 est avantageusement munie d'une partie aval 66 formant bride servant d'appui pour un joint d'étanchéité monté dans une bride 64 de cette enveloppe annulaire interne.The
Des orifices de passage 68, 70 ménagés dans les plates-formes métalliques externe 46 et interne 48 du distributeur 42 sont en outre prévus pour assurer un refroidissement des aubes fixes 44 du distributeur en entrée du rotor de la turbine haute pression à partir du comburant comprimé disponible en sortie du conduit de diffusion 18 et s'écoulant en deux flux F1, F2 de part et d'autre de la chambre de combustion 24. Ces flux de refroidissement seront au préalable passés entre les différents secteurs des viroles souples sectorisées métalliques interne et externe et en outre par des orifices de ventilation 56c, 60c pratiqués dans ces viroles au niveau de fentes de séparations 72, 74 entre secteurs (voir par exemple la
Afin d'assurer l'étanchéité des flux d'écoulement de gaz entre la chambre de combustion et le distributeur d'entrée de la turbine, la bride 64 de l'enveloppe annulaire interne comporte une rainure circulaire 76 pour recevoir un joint circulaire d'étanchéité de type « oméga » 78 destiné à assurer l'étanchéité entre cette bride de l'enveloppe annulaire interne et l'extrémité aval formant bride 66 de la virole métallique interne 48. Ainsi, le flux de comburant comprimé en provenance du compresseur et entourant la chambre par F2 ne peut rejoindre la turbine qu'au travers des orifices 70 (après avoir traversé les fentes de sectorisations 72 et les orifices de ventilation 56c). De même, la plate-forme circulaire externe du distributeur 46 comporte une bride 80 munie d'une gorge circulaire 82 pour recevoir un joint à lamelle 84 dont une extrémité va venir en contact avec l'enveloppe annulaire externe 12 pour assurer une étanchéité vis à vis. du flux F1 qui sera alors forcé de s'écouler au travers des orifices 68 (aussi après avoir traversé les fentes de sectorisation 74 et les orifices de ventilation 60c).In order to seal the flow of gas flow between the combustion chamber and the inlet distributor of the turbine, the
Claims (11)
- A turbomachine comprising a shell (12 , 14) of metal material containing, in a gas flow direction F: a fuel injection assembly (20; 22) ; a composite material combustion chamber (24) ; and a sectorized nozzle (42) of metal material forming the inlet stage with fixed blades (44) of a high pressure turbine, the turbomachine being characterized in that said combustion chamber is held in position by a sectorized flexible sleeve (56, 60) of metal material having a first end (56a, 60a) fixed by first fixing means (50 , 52) to said combustion chamber and having a flange-forming second end (56b, 60b) fixed to said shell by second fixing means (54, 58).
- A turbomachine according to claim 1, characterized in that said first fixing means also provide connection between said combustion chamber and said sectorized nozzle.
- A turbomachine according to claim 1 or claim 2, characterized in that said first fixing means are constituted by a plurality of bolts.
- A turbomachine according to claim 1, characterized in that said metal sectorized flexible sleeve has ventilation orifices (56c, 60c) for allowing a cooling fluid to pass through.
- A turbomachine according to claim 4, characterized in that said metal sectorized flexible sleeve has a plurality of parallel sectorizing slots (72, 74) terminating at the upstream ends of said ventilation orifices.
- A turbomachine according to claim 5, characterized in that said sectorizing slots are dimensioned to compensate for the thermal expansion that exists between the combustion chamber of composite material and the shell of metal material.
- A turbomachine comprising a shell having outer and inner annular walls (12, 14) of metal material defining between them a space (16) for receiving in succession, in the gas flow direction F: a fuel injection assembly (20; 22), and both an annular combustion chamber (24) of composite material formed by an outer axially-extending side wall (26), an inner axially-extending side wall (28), and a transversely-extending end wall (30), and also by a sectorized annular nozzle (42) of metal material formed by a plurality of fixed blades (44) mounted between an outer sectorized circular platform (46) and an inner sectorized circular platform (48), the turbomachine being characterized in that downstream ends (26a, 28a) of said outer and inner side walls of the combustion chamber are held in position by outer and inner sectorized flexible sleeves (56, 60) of metal material having first ends (56a, 60a) fixed to said outer and inner downstream ends by first fixing means (50, 52), and having flange-forming second ends (56b, 60b) fixed to said outer and inner annular shells by second fixing means (54, 58).
- A turbomachine according to claim 7, characterized in that said first fixing means comprise firstly first holding means (50) for holding said downstream end of the inner side wall of the combustion chamber between said inner sectorized circular platform of the nozzle and said first end of the inner sectorized flexible sleeve, and secondly second holding means (52) for holding said downstream end of the outer side wall of the combustion chamber between said outer sectorized circular platform of the nozzle and said first end of the outer sectorized flexible sleeve.
- A turbomachine according to claim 8, characterized in that said first and second holding means are constituted by a respective plurality of bolts.
- A turbomachine according to claim 7, characterized in that said first end of the inner sectorized flexible sleeve has a flange-forming downstream portion (66) serving as a bearing surface for a gasket (78) of said inner annular wall of the shell.
- A turbomachine according to claim 10, characterized in that said inner annular wall of the shell includes a flange (64) having a circular groove (76) receiving an omega type circular gasket (78) for providing sealing between said flange of the inner annular wall of the shell and said flange-forming downstream portion a
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0107375 | 2001-06-06 | ||
FR0107375A FR2825787B1 (en) | 2001-06-06 | 2001-06-06 | FITTING OF CMC COMBUSTION CHAMBER OF TURBOMACHINE BY FLEXIBLE LINKS |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1265030A1 EP1265030A1 (en) | 2002-12-11 |
EP1265030B1 true EP1265030B1 (en) | 2008-07-09 |
Family
ID=8863996
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP02291359A Expired - Lifetime EP1265030B1 (en) | 2001-06-06 | 2002-06-04 | Mounting of a ceramic matrix composite combustion chamber with flexible shrouds |
Country Status (5)
Country | Link |
---|---|
US (1) | US6823676B2 (en) |
EP (1) | EP1265030B1 (en) |
JP (1) | JP3984101B2 (en) |
DE (1) | DE60227455D1 (en) |
FR (1) | FR2825787B1 (en) |
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FR2871845B1 (en) * | 2004-06-17 | 2009-06-26 | Snecma Moteurs Sa | GAS TURBINE COMBUSTION CHAMBER ASSEMBLY WITH INTEGRATED HIGH PRESSURE TURBINE DISPENSER |
FR2871844B1 (en) * | 2004-06-17 | 2006-09-29 | Snecma Moteurs Sa | SEALED ASSEMBLY OF A HIGH PRESSURE TURBINE DISPENSER ON ONE END OF A COMBUSTION CHAMBER IN A GAS TURBINE |
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 |
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FR2913051B1 (en) * | 2007-02-28 | 2011-06-10 | Snecma | TURBINE STAGE IN A TURBOMACHINE |
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CN102128719B (en) * | 2010-12-13 | 2012-10-24 | 中国航空动力机械研究所 | Sectorial reverse flow combustor and split combustor case thereof |
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JP6614407B2 (en) | 2015-06-10 | 2019-12-04 | 株式会社Ihi | Turbine |
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 |
US10385776B2 (en) | 2017-02-23 | 2019-08-20 | General Electric Company | Methods for assembling a 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 |
FR3081027B1 (en) * | 2018-05-09 | 2020-10-02 | Safran Aircraft Engines | TURBOMACHINE INCLUDING AN AIR TAKE-OFF CIRCUIT |
CN111023154B (en) * | 2019-12-31 | 2024-08-30 | 新奥能源动力科技(上海)有限公司 | Fuel nozzle and combustion chamber |
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US11859819B2 (en) | 2021-10-15 | 2024-01-02 | General Electric Company | Ceramic composite combustor dome and liners |
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- 2002-06-04 DE DE60227455T patent/DE60227455D1/en not_active Expired - Lifetime
- 2002-06-04 EP EP02291359A patent/EP1265030B1/en not_active Expired - Lifetime
- 2002-06-05 US US10/161,805 patent/US6823676B2/en not_active Expired - Lifetime
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Also Published As
Publication number | Publication date |
---|---|
US6823676B2 (en) | 2004-11-30 |
JP2002372242A (en) | 2002-12-26 |
US20030000223A1 (en) | 2003-01-02 |
DE60227455D1 (en) | 2008-08-21 |
EP1265030A1 (en) | 2002-12-11 |
FR2825787A1 (en) | 2002-12-13 |
JP3984101B2 (en) | 2007-10-03 |
FR2825787B1 (en) | 2004-08-27 |
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