EP1265032A1 - Ceramic matrix composite material gas turbine combustion chamber - Google Patents

Ceramic matrix composite material gas turbine combustion chamber Download PDF

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Publication number
EP1265032A1
EP1265032A1 EP02291361A EP02291361A EP1265032A1 EP 1265032 A1 EP1265032 A1 EP 1265032A1 EP 02291361 A EP02291361 A EP 02291361A EP 02291361 A EP02291361 A EP 02291361A EP 1265032 A1 EP1265032 A1 EP 1265032A1
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EP
European Patent Office
Prior art keywords
combustion chamber
distributor
internal
external
envelope
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP02291361A
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German (de)
French (fr)
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EP1265032B1 (en
Inventor
Alexandre Forestier
Didier Hernandez
Eric Conete
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Safran Aircraft Engines SAS
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SNECMA Moteurs SA
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Publication of EP1265032A1 publication Critical patent/EP1265032A1/en
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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
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M2900/00—Special features of, or arrangements for combustion chambers
    • F23M2900/05002—Means for accommodate thermal expansion of the wall liner

Definitions

  • the present invention relates to the field of turbomachinery and more in particular it concerns the interface between the high pressure turbine and the combustion chamber of turbojets fitted with a combustion chamber CMC (ceramic matrix composite).
  • CMC ceramic matrix composite
  • the high pressure turbine including its inlet distributor (HPT nozzle), the combustion chamber as well as the casing (also called envelope) of this chamber are made in a same material, usually metallic.
  • HPT nozzle inlet distributor
  • the combustion chamber as well as the casing (also called envelope) of this chamber are made in a same material, usually metallic.
  • metallic materials and composite materials have very different coefficients of thermal expansion. This results in particularly acute interface problems at the level of the distributor, at the inlet of the high pressure turbine, and of connection with the casing of the bedroom.
  • the present invention overcomes these drawbacks by proposing a connection housing-chamber having the capacity to absorb the displacements induced by differences in the expansion coefficients of these parts.
  • An object of the invention is also to propose a structure of simple form and the manufacture of which is particularly easy.
  • a turbomachine comprising, in a envelope of metallic material and in a direction F of gas flow, a fuel injection assembly, a material combustion chamber composite and a distributor of metallic material forming the input stage to fixed blades of a high pressure turbine, and said distributor being supported by said envelope and fixed thereto by first removable fixing means, characterized in that said combustion chamber is mounted floating in said envelope and held in position by the only said distributor to which it is fixed elastically by second removable fixing means.
  • the first removable fixing means are suitable for allow free radial expansion of said dispenser relative to said envelope.
  • said second means of removable fasteners comprise firstly first holding means for pinch hold an internal axial end wall of said chamber combustion between an internal circular distributor platform and a flange serving as a support for an internal annular wall of said envelope and of the second holding means for holding a wall with elastic preload axial external end of said combustion chamber on a platform external circular of the distributor.
  • the support flange is sectorized to compensate for deviations circumferential geometries resulting from the differential expansion existing at high temperatures between said internal circular platform of the dispenser and said internal axial wall of the combustion chamber.
  • This support flange is mounted between a flange of said inner annular wall of the envelope and a ferrule of metallic material held against this flange by said first removable fixing means.
  • said first removable fixing means comprise a plurality of bolts, each of the screw axes which passes through a corresponding oblong hole of said support flange is provided with a shoulder on which is supported on said ferrule so as to allow sliding of said support flange between said ferrule and said flange of the internal annular wall of the envelope.
  • said flange of the wall inner annular of the envelope has a circular groove for receiving a "omega" type circular seal designed to seal between this said flange of the internal annular wall of the envelope and said support flange.
  • a ferrule of composite material advantageously brazed on said external end wall of the combustion chamber is maintained with a elastic prestress against said external circular platform of the distributor by the second holding means, said ferrule comprising a groove circular to receive an omega-type circular seal intended for sealing between said outer end wall of the combustion and said external circular platform of the distributor.
  • this space 16 comprising, in the direction of flow of the gases, first of all an injection assembly formed by a plurality of injection systems 20 and regularly distributed around the duct 18 and each comprising a nozzle fuel injection 22 fixed to the outer annular casing 12 (in a to simplify the drawings, the mixer and the deflector associated with each injection nozzle have not been shown), then a combustion chamber in high temperature composite material 24, of CMC type or others (carbon by example), formed of an external axial wall 26 and an internal axial wall 28, both coaxial with axis 10, and a transverse wall 30 which constitutes the bottom of this combustion chamber and which has flaps 32, 34 fixed by all suitable means, for example metal or refractory head bolts conical), on upstream ends 36, 38 of the axial walls 26, 28, this bottom of the chamber 30 being provided with orifices 40 to allow the injection of fuel and of a part of the oxidizer in the combustion chamber 24, and finally a annular distributor 42 of metallic material forming an inlet stage of a high pressure turbine (not shown) and conventionally
  • the combustion chamber is mounted floating in the annular casing and held in position by the only distributor to whom it is fixed elastically by second removable fixing means which on the one hand have first holding means 52 for holding by pinch an internal axial end wall 54 of the combustion chamber (opposite the upstream end 38) between the internal circular platform of the distributor 48 and a flange 56 serving to support the internal annular casing 14 and second holding means 58 for holding with a prestress elastic 60 an external axial end wall 62 of said chamber combustion (opposite the upstream end 36) on the external circular platform distributor 46.
  • the support flange 56 is mounted between a flange 64 of the internal annular casing 14 and a ferrule made of metallic material 66 held against this flange by the first removable fixing means 50.
  • Passage holes 68, 70 for the passage of compressed oxidizer previously separated, at the outlet of the diffusion duct 18, into at least two streams distinct F1, F2 flowing on either side of the combustion chamber 24 (and ensuring in particular its cooling), are provided in the platforms metallic 46 and internal 48 of the distributor 42 to ensure cooling of the stationary vanes 44 of the distributor at the inlet of the turbine rotor high pressure.
  • the combustion chamber 24 having a coefficient of thermal expansion very different from the other metal parts forming the turbomachine, in particular the distributor 42 to which it is fixed and the annular casing 12, 14, it is provided that the first removable fixing means 50 are adapted to allow at high temperatures, a free radial expansion of the dispenser relative to the annular envelope.
  • the support flange 56 is pierced with holes oblongs 72 intended to cooperate with the screw axes of the plurality of bolts 50 one shoulder 74 of which serves to support the ferrule 66 so as to allow sliding of this support flange between the ferrule and the flange 64 of the casing internal annular 14.
  • this flange is sectorized to compensate for deviations circumferential geometries resulting from the differential expansion existing at these high temperatures between the internal circular platform 48 of the dispenser and the internal axial wall 28, 54 of the combustion chamber.
  • the flange of the internal annular casing 64 comprises a circular groove 76 for receiving a type circular seal "Omega" 78 intended to seal between this flange of the envelope internal annular and the support flange 56.
  • the external circular platform dispenser 46 has a flange 80 provided with a circular groove 82 for receive a lamellar seal 84 one end of which will come into contact with the outer annular casing 12 to seal against the flow F1.
  • the seal between the combustion chamber 24 and the distributor 42 it is provided between the outer end wall of the combustion chamber 62 and the external circular platform of the distributor 46 also by means of a "Omega" type 86 seal mounted in a groove circular 88 of a ferrule made of composite material 90, advantageously brazed on the outer end wall of the combustion chamber 62, and held with elastic preload (obtained for example by spring 60) against the platform external circular of the distributor 46 by the second holding means 58.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The gas turbine engine combustion chamber has an annular metal casing (12,14), a fuel injector assembly and a composite combustion chamber (24). There is a metallic distributor (42) forming an inlet stage with fixed vanes (44) for a high pressure turbine and attached by movable fixings (50). The combustion chamber is mounted floatingly in the casing and held in position with respect to the distributor by movable fixings (52,58,60).

Description

Domaine de l'inventionField of the invention

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 un même matériau, généralement 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 de ces matériaux et leur coût 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 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 a same material, usually metallic. However, in some special conditions of use using temperatures of significantly higher combustion, the use of a metal chamber proves to be totally unsuitable thermal point of view and it must be resorted to a room based on CMC type high temperature composite materials. However, difficulties in using these materials and their cost make their use is most often limited to the combustion chamber itself, the distributor inlet of the high pressure turbine and the remaining casing then produced more conventionally made of metallic materials. However, metallic materials and composite materials have very different coefficients of thermal expansion. This results in particularly acute interface problems at the level of the distributor, at the inlet of the high pressure turbine, and of connection with the casing of the bedroom.

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 en matériau métallique formant l'étage d'entrée à aubes fixes d'une turbine haute pression, et ledit distributeur étant supporté par ladite enveloppe et fixé à celle-ci par des premiers moyens de fixation amovibles, caractérisée en ce que ladite chambre de combustion est montée flottante dans ladite enveloppe et maintenue en position par le seul dit distributeur auquel elle est fixée de façon élastique par des seconds moyens de fixation amovibles.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 distributor of metallic material forming the input stage to fixed blades of a high pressure turbine, and said distributor being supported by said envelope and fixed thereto by first removable fixing means, characterized in that said combustion chamber is mounted floating in said envelope and held in position by the only said distributor to which it is fixed elastically by second removable fixing means.

Par ce rattachement direct (intégration) de la chambre de combustion au distributeur, sans liaison avec l'enveloppe, on simplifie notablement la fabrication de cette chambre tout en améliorant particulièrement l'étanchéité chambre-distributeur. En outre, le parfait alignement de la veine qui en résulte en fonctionnement permet une meilleure alimentation de la turbine haute pression. La suppression des habituelles brides de la chambre de combustion (pour la liaison à l'enveloppe) procure de plus un gain de masse appréciable pour cette chambre et donc pour la turbomachine.By this direct connection (integration) of the combustion chamber to distributor, without connection to the envelope, the production is considerably simplified of this chamber while particularly improving the sealing chamber-distributor. In addition, the perfect alignment of the resulting vein operation allows better supply of the high pressure turbine. The removal of the usual flanges from the combustion chamber (for connection to the envelope) also provides an appreciable gain in mass for this chamber and so for the turbomachine.

L'intégration du distributeur sur la chambre reportant les problèmes de déplacement relatif entre cette dernière et l'enveloppe au niveau du distributeur, il est prévu que les premiers moyens de fixation amovibles sont adaptés pour permettre une libre dilatation radiale dudit distributeur par rapport à ladite enveloppe.The integration of the dispenser on the chamber reporting the problems of relative displacement between the latter and the envelope at the distributor, it it is intended that the first removable fixing means are suitable for allow free radial expansion of said dispenser relative to said envelope.

Selon un mode de réalisation préférentiel, lesdits seconds moyens de fixation amovibles comportent d'une part des premiers moyens de maintien pour maintenir par pincement une paroi axiale interne d'extrémité de ladite chambre de combustion entre une plate-forme circulaire interne du distributeur et une bride servant de support à une paroi annulaire interne de ladite enveloppe et des seconds moyens de maintien pour maintenir avec une précontrainte élastique une paroi axiale externe d'extrémité de ladite chambre de combustion sur une plate-forme circulaire externe du distributeur.According to a preferred embodiment, said second means of removable fasteners comprise firstly first holding means for pinch hold an internal axial end wall of said chamber combustion between an internal circular distributor platform and a flange serving as a support for an internal annular wall of said envelope and of the second holding means for holding a wall with elastic preload axial external end of said combustion chamber on a platform external circular of the distributor.

De préférence, la bride support est sectorisée pour compenser les écarts géométriques circonférenciels résultant de la dilatation différentielle existant aux températures élevées entre ladite plate-forme circulaire interne du distributeur et ladite paroi axiale interne de la chambre de combustion. Cette bride support est montée entre une bride de ladite paroi annulaire interne de l'enveloppe et une virole en matériau métallique maintenue contre cette bride par lesdits premiers moyens de fixation amovibles.Preferably, the support flange is sectorized to compensate for deviations circumferential geometries resulting from the differential expansion existing at high temperatures between said internal circular platform of the dispenser and said internal axial wall of the combustion chamber. This support flange is mounted between a flange of said inner annular wall of the envelope and a ferrule of metallic material held against this flange by said first removable fixing means.

Avantageusement, lesdits premiers moyens de fixation amovibles comportent une pluralité de boulons dont chacun des axes de vis qui traverse un trou oblong correspondant de ladite bride support est muni d'un épaulement sur lequel est mis en appui ladite virole de façon à permettre un coulissement de ladite bride support entre ladite virole et ladite bride de la paroi annulaire interne de l'enveloppe.Advantageously, said first removable fixing means comprise a plurality of bolts, each of the screw axes which passes through a corresponding oblong hole of said support flange is provided with a shoulder on which is supported on said ferrule so as to allow sliding of said support flange between said ferrule and said flange of the internal annular wall of the envelope.

Pour assurer l'étanchéité de la turbomachine, ladite bride de la paroi annulaire interne de l'enveloppe comporte une rainure circulaire pour 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 bride support. De même, une virole en matériau composite avantageusement brasée sur ladite paroi externe d'extrémité de la chambre de combustion est maintenue avec une précontrainte élastique contre ladite plate-forme circulaire externe du distributeur par les seconds moyens de maintien, ladite virole comportant une rainure circulaire pour recevoir un joint circulaire d'étanchéité de type « oméga » destiné à assurer l'étanchéité entre ladite paroi externe d'extrémité de la chambre de combustion et ladite plate-forme circulaire externe du distributeur.To seal the turbomachine, said flange of the wall inner annular of the envelope has a circular groove for receiving a "omega" type circular seal designed to seal between this said flange of the internal annular wall of the envelope and said support flange. Similarly, a ferrule of composite material advantageously brazed on said external end wall of the combustion chamber is maintained with a elastic prestress against said external circular platform of the distributor by the second holding means, said ferrule comprising a groove circular to receive an omega-type circular seal intended for sealing between said outer end wall of the combustion and said external circular platform of the distributor.

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,
  • la figure 3 montre en perspective détaillée la liaison turbine haute pression - chambre de combustion au niveau de la plate-forme externe du distributeur, et
  • la figure 4 est une vue selon IV de la figure 1.
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,
  • 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, and
  • FIG. 4 is a view along IV of FIG. 1.

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 et 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 en matériau composite haute température 24, 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 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 externe 46 et une plate-forme circulaire interne 48. Le distributeur repose sur des moyens support 49 solidaire de l'enveloppe annulaire de la turbomachine et est il fixé à celle-ci par des premiers moyens de fixation amovibles constitués de préférence par une pluralité de boulons 50.this space 16 comprising, in the direction of flow of the gases, first of all an injection assembly formed by a plurality of injection systems 20 and regularly distributed around the duct 18 and each comprising a nozzle fuel injection 22 fixed to the outer annular casing 12 (in a to simplify the drawings, the mixer and the deflector associated with each injection nozzle have not been shown), then a combustion chamber in high temperature composite material 24, of CMC type or others (carbon by example), formed of an external axial wall 26 and an internal axial wall 28, both coaxial with axis 10, and a transverse wall 30 which constitutes the bottom of this combustion chamber and which has flaps 32, 34 fixed by all suitable means, for example metal or refractory head bolts conical), on upstream ends 36, 38 of the axial walls 26, 28, this bottom of the chamber 30 being provided with orifices 40 to allow the injection of fuel and of a part of the oxidizer in the combustion chamber 24, and finally a annular distributor 42 of metallic material forming an inlet stage of a high pressure turbine (not shown) and conventionally comprising a plurality stationary vanes 44 mounted between an external circular platform 46 and a platform internal circular 48. The dispenser rests on support means 49 secured to the annular casing of the turbomachine and is fixed thereto by first removable fixing means preferably constituted by a plurality of bolts 50.

Selon l'invention, la chambre de combustion est montée flottante dans l'enveloppe annulaire et maintenue en position par le seul distributeur auquel elle est fixée de façon élastique par des seconds moyens de fixation amovibles qui comportent d'une part des premiers moyens de maintien 52 pour maintenir par pincement une paroi axiale interne d'extrémité 54 de la chambre de combustion (opposée à l'extrémité amont 38) entre la plate-forme circulaire interne du distributeur 48 et une bride 56 servant de support à l'enveloppe annulaire interne 14 et des seconds moyens de maintien 58 pour maintenir avec une précontrainte élastique 60 une paroi axiale externe d'extrémité 62 de ladite chambre de combustion (opposée à l'extrémité amont 36) sur la plate-forme circulaire externe du distributeur 46. La bride support 56 est montée entre une bride 64 de l'enveloppe annulaire interne 14 et une virole en matériau métallique 66 maintenue contre cette bride par les premiers moyens de fixation amovibles 50.According to the invention, the combustion chamber is mounted floating in the annular casing and held in position by the only distributor to whom it is fixed elastically by second removable fixing means which on the one hand have first holding means 52 for holding by pinch an internal axial end wall 54 of the combustion chamber (opposite the upstream end 38) between the internal circular platform of the distributor 48 and a flange 56 serving to support the internal annular casing 14 and second holding means 58 for holding with a prestress elastic 60 an external axial end wall 62 of said chamber combustion (opposite the upstream end 36) on the external circular platform distributor 46. The support flange 56 is mounted between a flange 64 of the internal annular casing 14 and a ferrule made of metallic material 66 held against this flange by the first removable fixing means 50.

Des orifices de passage 68, 70 pour le passage du comburant comprimé préalablement séparé, en sortie du conduit de diffusion 18, en au moins deux flux distincts F1, F2 s'écoulant de part et d'autre de la chambre de combustion 24 (et assurant notamment son refroidissement), sont ménagés dans les plates-formes métalliques externe 46 et interne 48 du distributeur 42 pour assurer un refroidissement des aubes fixes 44 du distributeur en entrée du rotor de la turbine haute pression.Passage holes 68, 70 for the passage of compressed oxidizer previously separated, at the outlet of the diffusion duct 18, into at least two streams distinct F1, F2 flowing on either side of the combustion chamber 24 (and ensuring in particular its cooling), are provided in the platforms metallic 46 and internal 48 of the distributor 42 to ensure cooling of the stationary vanes 44 of the distributor at the inlet of the turbine rotor high pressure.

La chambre de combustion 24 ayant un coefficient de dilatation thermique très différent des autres pièces métalliques formant la turbomachine, notamment le distributeur 42 auquel elle est fixée et l'enveloppe annulaire 12, 14, il est prévu que les premiers moyens de fixation amovibles 50 soient adaptés pour permettre aux températures élevées une libre dilatation radiale du distributeur par rapport à l'enveloppe annulaire. Pour ce faire, la bride support 56 est percée de trous oblongs 72 destinés à coopérer avec les axes de vis de la pluralité de boulons 50 dont un épaulement 74 sert d'appui à la virole 66 de façon à permettre un coulissement de cette bride support entre la virole et la bride 64 de l'enveloppe annulaire interne 14. En outre, cette bride est sectorisée pour compenser les écarts géométriques circonférenciels résultant de la dilatation différentielle existant à ces températures élevées entre la plate-forme circulaire interne 48 du distributeur et la paroi axiale interne 28, 54 de la chambre de combustion.The combustion chamber 24 having a coefficient of thermal expansion very different from the other metal parts forming the turbomachine, in particular the distributor 42 to which it is fixed and the annular casing 12, 14, it is provided that the first removable fixing means 50 are adapted to allow at high temperatures, a free radial expansion of the dispenser relative to the annular envelope. To do this, the support flange 56 is pierced with holes oblongs 72 intended to cooperate with the screw axes of the plurality of bolts 50 one shoulder 74 of which serves to support the ferrule 66 so as to allow sliding of this support flange between the ferrule and the flange 64 of the casing internal annular 14. In addition, this flange is sectorized to compensate for deviations circumferential geometries resulting from the differential expansion existing at these high temperatures between the internal circular platform 48 of the dispenser and the internal axial wall 28, 54 of the combustion chamber.

Afin d'assurer l'étanchéité des flux d'écoulement de gaz entre la chambre de combustion et la turbine, la bride de l'enveloppe annulaire interne 64 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 la bride support 56. 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. 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.To seal the gas flow between the chamber combustion chamber and the turbine, the flange of the internal annular casing 64 comprises a circular groove 76 for receiving a type circular seal "Omega" 78 intended to seal between this flange of the envelope internal annular and the support flange 56. 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. Likewise, the external circular platform dispenser 46 has a flange 80 provided with a circular groove 82 for receive a lamellar seal 84 one end of which will come into contact with the outer annular casing 12 to seal against the flow F1.

Quant à l'étanchéité entre la chambre de combustion 24 et le distributeur 42 elle est assurée entre la paroi externe d'extrémité de la chambre de combustion 62 et la plate-forme circulaire externe du distributeur 46 également au moyen d'un joint circulaire d'étanchéité de type « oméga » 86 montée dans une rainure circulaire 88 d'une virole en matériau composite 90, avantageusement brasée sur la paroi externe d'extrémité de la chambre de combustion 62, et maintenue avec une précontrainte élastique (obtenue par exemple par le ressort 60) contre la plate-forme circulaire externe du distributeur 46 par les seconds moyens de maintien 58.As for the seal between the combustion chamber 24 and the distributor 42 it is provided between the outer end wall of the combustion chamber 62 and the external circular platform of the distributor 46 also by means of a "Omega" type 86 seal mounted in a groove circular 88 of a ferrule made of composite material 90, advantageously brazed on the outer end wall of the combustion chamber 62, and held with elastic preload (obtained for example by spring 60) against the platform external circular of the distributor 46 by the second holding means 58.

Claims (10)

Turbomachine comportant, dans une enveloppe en matériau métallique (12, 14) et selon un sens F d'écoulement des gaz, un ensemble d'injection d'un carburant (20 ; 22), une chambre de combustion en matériau composite (24) et un distributeur en matériau métallique (42) formant l'étage d'entrée à aubes fixes (44) d'une turbine haute pression, et ledit distributeur étant supporté par ladite enveloppe et fixé à celle-ci par des premiers moyens de fixation amovibles (50), caractérisée en ce que ladite chambre de combustion est montée flottante dans ladite enveloppe et maintenue en position par le seul dit distributeur auquel elle est fixée de façon élastique par des seconds moyens de fixation amovibles (52, 58, 60).Turbomachine 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 made of metallic material (42) forming the inlet stage with fixed blades (44) of a high pressure turbine, and said distributor being supported by said casing and fixed to it by first removable fixing means (50), characterized in that said combustion chamber is mounted floating in said envelope and held in position by the only said distributor to which it is fixed elastically by second removable fixing means (52, 58, 60). Turbomachine selon la revendication 1, caractérisée en ce que lesdits premiers moyens de fixation amovibles sont adaptés pour permettre une libre dilatation radiale dudit distributeur par rapport à ladite enveloppe.Turbomachine according to claim 1, characterized in that said first removable fixing means are adapted to allow free radial expansion of said distributor relative to said envelope. Turbomachine selon la revendication 1, caractérisée en ce que lesdits seconds moyens de fixation amovibles comportent d'une part des premiers moyens de maintien (52) pour maintenir par pincement une paroi axiale interne d'extrémité (54) de ladite chambre de combustion entre une plate-forme circulaire interne du distributeur (48) et une bride (56) servant de support à une paroi annulaire interne (14) de ladite enveloppe et des seconds moyens de maintien (58) pour maintenir avec une précontrainte élastique (60) une paroi axiale externe d'extrémité (62) de ladite chambre de combustion sur une plate-forme circulaire externe du distributeur (46).Turbomachine according to claim 1, characterized in that said second removable fixing means comprise on the one hand first holding means (52) for holding by pinching an internal axial end wall (54) of said combustion chamber between a internal circular platform of the distributor (48) and a flange (56) serving to support an internal annular wall (14) of said casing and second holding means (58) for holding a wall with elastic preload (60) axial external end (62) of said combustion chamber on an external circular platform of the distributor (46). Turbomachine selon la revendication 3, caractérisée en ce que ladite bride support est sectorisée pour compenser les écarts géométriques circonférenciels résultant de la dilatation différentielle existant aux températures élevées entre ladite plate-forme circulaire interne du distributeur et ladite paroi axiale interne de la chambre de combustion.Turbomachine according to claim 3, characterized in that said support flange is sectorized to compensate for the circumferential geometric deviations resulting from the differential expansion existing at high temperatures between said internal circular platform of the distributor and said internal axial wall of the combustion chamber. Turbomachine selon la revendication 3, caractérisée en ce que ladite bride support est montée entre une bride (64) de ladite paroi annulaire interne de l'enveloppe et une virole en matériau métallique (66) maintenue contre cette bride par lesdits premiers moyens de fixation amovibles.Turbomachine according to claim 3, characterized in that said support flange is mounted between a flange (64) of said inner annular wall of the envelope and a ferrule made of metallic material (66) held against this flange by said first removable fixing means . Turbomachine selon la revendication 5, caractérisée en ce que lesdits premiers moyens de fixation amovibles comportent une pluralité de boulons (50) dont chacun des axes de vis qui traverse un trou oblong correspondant (72) de ladite bride support est muni d'un épaulement (74) sur lequel est mis en appui ladite virole de façon à permettre un coulissement de ladite bride support entre ladite virole et ladite bride de la paroi annulaire interne de l'enveloppe.Turbomachine according to claim 5, characterized in that said first removable fixing means comprise a plurality of bolts (50), each of the screw axes which passes through a corresponding oblong hole (72) of said support flange is provided with a shoulder ( 74) on which said ferrule is supported so as to allow said support flange to slide between said ferrule and said flange of the internal annular wall of the envelope. Turbomachine selon la revendication 6, caractérisée en ce que ladite bride de la paroi annulaire interne de l'enveloppe comporte une rainure circulaire (76) pour recevoir un joint circulaire d'étanchéité de type « oméga » (78) destiné à assurer l'étanchéité entre cette dite bride de la paroi annulaire interne de l'enveloppe et ladite bride support.Turbomachine according to claim 6, characterized in that said flange of the internal annular wall of the envelope comprises a circular groove (76) for receiving a circular seal of type "omega" type (78) intended to ensure sealing between this said flange of the internal annular wall of the envelope and said support flange. Turbomachine selon la revendication 3, caractérisée en ce qu'elle comporte en outre une virole en matériau composite (90) avantageusement brasée sur ladite paroi externe d'extrémité de la chambre de combustion et maintenue avec une précontrainte élastique (60) contre ladite plate-forme circulaire externe du distributeur par lesdits seconds moyens de maintien.Turbomachine according to claim 3, characterized in that it further comprises a ferrule made of composite material (90) advantageously brazed on said external end wall of the combustion chamber and held with an elastic preload (60) against said platform. external circular shape of the dispenser by said second holding means. Turbomachine selon la revendication 8, caractérisée en ce que ladite virole comporte une rainure circulaire (88) pour recevoir un joint circulaire d'étanchéité de type « oméga » (86) destiné à assurer l'étanchéité entre ladite paroi externe d'extrémité de la chambre de combustion et ladite plate-forme circulaire externe du distributeur.Turbomachine according to claim 8, characterized in that said ferrule comprises a circular groove (88) for receiving a circular seal of type "omega" type (86) intended to seal between said outer end wall of the combustion chamber and said external circular platform of the distributor. Turbomachine comprenant une enveloppe annulaire externe (12) et une enveloppe annulaire interne (14) délimitant entre elles un espace (16) pour recevoir successivement, dans le sens F d'écoulement des gaz, d'une part une chambre de combustion annulaire (24) en matériau composite formée d'une paroi axiale externe (26), d'une paroi axiale interne (28) et d'une paroi transversale (30) qui constitue le fond de cette chambre de combustion, et d'autre part un distributeur annulaire sectorisé (42) en matériau métallique formé d'une pluralité d'aubes fixes (44) montées entre une plate-forme axiale externe (46) et une plate-forme axiale interne (48), caractérisée en ce que les parties d'extrémité libres (54, 62) desdites parois axiales externe et interne de la chambre de combustion sont reliées auxdites plates-formes externe et interne du distributeur, ladite paroi axiale interne d'extrémité (54) de la chambre étant pincée au moyen de premiers moyens de maintien (52) entre ladite plate-forme interne du distributeur et une bride (56) servant de support à ladite enveloppe annulaire interne, et ladite paroi axiale externe d'extrémité (62) de la chambre étant maintenue avec une précontrainte élastique (60) contre ladite plate-forme externe du distributeur par des seconds moyens de maintien (58).Turbomachine comprising an external annular envelope (12) and an internal annular envelope (14) delimiting between them a space (16) for successively receiving, in the direction F of gas flow, on the one hand an annular combustion chamber (24 ) made 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 distributor sectored annular (42) of metallic material formed of a plurality of fixed vanes (44) mounted between an external axial platform (46) and an internal axial platform (48), characterized in that the parts of free ends (54, 62) of said external and internal axial walls of the combustion chamber are connected to said external and internal platforms of the distributor, said internal axial end wall (54) of the chamber being pinched by means of first means holding (52) between the said internal distributor platform and a flange (56) serving as a support for said internal annular envelope, and said external axial end wall (62) of the chamber being held with an elastic preload (60) against said platform external of the dispenser by second holding means (58).
EP02291361A 2001-06-06 2002-06-04 Ceramic matrix composite material gas turbine combustion chamber Expired - Lifetime EP1265032B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0107360A FR2825780B1 (en) 2001-06-06 2001-06-06 COMBUSTION CHAMBER ARCHITECURE OF CERAMIC MATRIX MATERIAL
FR0107360 2001-06-06

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EP1265032B1 EP1265032B1 (en) 2004-10-06

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JP3983603B2 (en) 2007-09-26
JP2003035104A (en) 2003-02-07
EP1265032B1 (en) 2004-10-06
FR2825780B1 (en) 2003-08-29
FR2825780A1 (en) 2002-12-13
US20020184891A1 (en) 2002-12-12
DE60201467T2 (en) 2006-03-09
DE60201467D1 (en) 2004-11-11
US6679062B2 (en) 2004-01-20

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