EP1265030A1 - Mounting of a metallic matrix composite combustion chamber with flexible linking shrouds - Google Patents

Mounting of a metallic matrix composite combustion chamber with flexible linking shrouds Download PDF

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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
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EP
European Patent Office
Prior art keywords
internal
combustion chamber
external
sectored
flexible
Prior art date
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Granted
Application number
EP02291359A
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German (de)
French (fr)
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EP1265030B1 (en
Inventor
Eric Conete
Alexandre Forestier
Didier Hernandez
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Safran Aircraft Engines SAS
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SNECMA Moteurs SA
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Publication of EP1265030A1 publication Critical patent/EP1265030A1/en
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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
    • 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).

Abstract

The aircraft gas turbine engine is held in position be a flexible connecting ring which is made of metal in sectors (56,60). One end (56a,60a) of the ring is fixed (50,52) to the combustion chamber and the second end, which forms a flange, is fixed (54,58) to the envelope. The ring can be bolted to the combustion chamber. the connecting ring can be apertured for ventilation.

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 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).

Art antérieurPrior art

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.Conventionally, in a turbomachine, 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. However, under certain specific conditions of use implementing notably combustion temperatures the use of a metal chamber proves from a thermal point of view totally unsuitable and it must be resorted to a chamber based on materials CMC type high temperature composites. However, the difficulties of implementing work and the cost of these materials make their use most often limited to the combustion chamber itself, the inlet distributor of the high pressure turbine and the remaining casing then produced more conventionally in metallic materials. Gold, metallic materials and composite materials have very different coefficients of thermal expansion. It follows, from a point from an aerodynamic point of view, particularly acute interface problems at the level of the distributor, at the inlet of the high pressure turbine, and of connection with the casing from the room.

Objet et définition de l'inventionObject and definition of the invention

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 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.

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 aims are achieved by 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.

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 distributor, any misalignment of the gas stream in operation is avoided (thus guaranteeing a better supply of the high pressure turbine) while improving the chamber-distributor seal. The binding to the envelope by a flexible segmented ferrule system also provides weight savings appreciable for the combustion chamber compared to connecting devices traditional with heavy rigid flanges.

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 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.

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 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.

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 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.

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 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.

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 seal the turbomachine, 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.

Brève description des dessinsBrief description of the drawings

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 characteristics and advantages of the present invention will emerge more clearly from the following description, given by way of non-limiting illustration, with reference to the appended drawings in which:
  • FIG. 1 is a schematic view in axial half-section of a central part of a turbomachine,
  • FIG. 2 shows in detailed perspective the connection between the high pressure turbine and the combustion chamber at the level of the internal platform of the distributor, and
  • FIG. 3 shows in detailed perspective the connection between the high pressure turbine and the combustion chamber at the level of the external platform of the distributor.

Description détaillée d'un mode de réalisation préférentielDetailed description of a preferred embodiment

La figure 1 montre en demi-coupe axiale une partie centrale d'un turboréacteur ou d'un turbopropulseur (appelé turbomachine dans la suite de la description) comprenant :

  • 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,
FIG. 1 shows in axial half-section a central part of a turbojet engine or a turboprop engine (called a turbomachine in the following description) comprising:
  • an envelope comprising an external annular wall (or external casing) 12 of metallic material, of longitudinal axis 10, and an internal annular wall (or external casing) coaxial 14 also of metallic material,
  • an annular space 16 comprised between the two annular walls 12, 14 of this envelope receiving the compressed oxidizer, generally air, coming upstream of a compressor (not shown) of the turbomachine, through an annular duct of 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 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 a plurality of fixed vanes 44 mounted between a platform external sectored circular 46 and an internal sectored circular platform 48.

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 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. Thus, 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.

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, 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.

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 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.

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 like 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 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.

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 figure 3). Ces fentes de sectorisation sont dimensionnées de façon déterminée pour compenser la dilatation thermique existant entre la chambre de combustion en matériau composite et l'enveloppe en matériau métallique.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.

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).To seal the gas flow between the chamber of combustion and the turbine inlet distributor, 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. Thus, the flow of compressed oxidizer in coming from the compressor and surrounding the room by F2 cannot reach the turbine than through orifices 70 (after passing through the slots of sectorizations 72 and the ventilation openings 56c). Likewise, 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).

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 comprising, in an envelope of metallic material (12, 14) and in a direction F of gas flow, a fuel injection assembly (20,22), a combustion chamber of composite material (24) , and a distributor sectorized in metallic material (42) forming the input stage with fixed blades (44) of a high pressure turbine, characterized in that said combustion chamber is held in position by a flexible ferrule sectorized in material metallic (56, 60) of which a first end (56a, 60a) is fixed by first fixing means (50, 52) to said combustion chamber and of which a second flange end (56b, 60b) is fixed to said casing by second fixing means (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 according to claim 1, characterized in that said first fixing means also ensure the connection of said combustion chamber with said sectored distributor. 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 according to claim 1 or claim 2, characterized in that said first fixing means are constituted by a plurality of bolts. 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 according to claim 1, characterized in that said flexible metallic sectored ferrule comprises ventilation orifices (56c, 60c) to allow the passage of a cooling fluid. 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 according to claim 4, characterized in that said flexible metallic sectored ferrule comprises a plurality of parallel sectoring slots (72, 74) ending at the most upstream of said ventilation orifices. 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 according to claim 5, characterized in that said sectoring slots are dimensioned to compensate for the thermal expansion existing between the combustion chamber of composite material and the envelope of metallic material. 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 comprising an envelope having external (12) and internal (14) annular walls of metallic material delimiting between them a space (16) for successively receiving, in the direction F of gas flow, an injection assembly of a fuel (20, 22), and on the one hand an annular combustion chamber (24) of composite material formed by an external axial wall (26), an internal axial wall (28) and a transverse wall ( 30) which constitutes the bottom of this combustion chamber, and on the other hand a sectored annular distributor (42) of metallic material formed by a plurality of fixed vanes (44) mounted between an external sectorized circular platform (46 ) and an internal sectored circular platform (48), characterized in that downstream ends (26a, 28a) of said external and internal axial walls of the combustion chamber are held in position by flexible externalized and internal sectored ferrules made of material metallic (56, 60) whose first ends (56a, 60a) are fixed by first fixing means (50, 52) to said external and internal downstream ends and whose second ends forming flanges (56b, 60b) are fixed to said annular envelopes external and internal by second fixing means (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 according to claim 7, characterized in that said first fixing means comprise on the one hand first holding means (50) for holding said downstream end of the internal axial wall of the combustion chamber between said sectored circular platform internal of the distributor and said first end of the internal sectorized flexible ferrule and on the other hand second holding means (52) for maintaining said downstream end of the external axial wall of the combustion chamber between said external sectorized circular platform of the distributor and said first end of the external sectored flexible shell. Turbomachine selon la revendication 8, caractérisée en ce que lesdits premiers et seconds moyens de maintien sont constitués par une pluralité de boulons.Turbomachine according to claim 8, characterized in that said first and second holding means are constituted by a plurality of bolts. 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 according to claim 7, characterized in that said first end of the internal sectored flexible ferrule comprises a downstream part forming a flange (66) and serving as a support for a seal (78) of said internal annular wall of the envelope. 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.Turbomachine according to claim 10, characterized in that said internal annular wall of the envelope comprises a flange (64) of which a circular groove (76) receives a circular seal of type "omega" type (78) intended to ensure the sealing between said flange of the internal annular wall of the envelope and said downstream part forming flange.
EP02291359A 2001-06-06 2002-06-04 Mounting of a ceramic matrix composite combustion chamber with flexible shrouds Expired - Lifetime EP1265030B1 (en)

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FR0107375 2001-06-06
FR0107375A FR2825787B1 (en) 2001-06-06 2001-06-06 FITTING OF CMC COMBUSTION CHAMBER OF TURBOMACHINE BY FLEXIBLE LINKS

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DE60227455D1 (en) 2008-08-21
US6823676B2 (en) 2004-11-30
JP2002372242A (en) 2002-12-26
US20030000223A1 (en) 2003-01-02
FR2825787B1 (en) 2004-08-27
EP1265030B1 (en) 2008-07-09
JP3984101B2 (en) 2007-10-03
FR2825787A1 (en) 2002-12-13

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