EP1265032B1 - 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
EP1265032B1
EP1265032B1 EP02291361A EP02291361A EP1265032B1 EP 1265032 B1 EP1265032 B1 EP 1265032B1 EP 02291361 A EP02291361 A EP 02291361A EP 02291361 A EP02291361 A EP 02291361A EP 1265032 B1 EP1265032 B1 EP 1265032B1
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EP
European Patent Office
Prior art keywords
combustion chamber
flange
nozzle
shell
turbomachine according
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.)
Expired - Lifetime
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EP02291361A
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German (de)
French (fr)
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EP1265032A1 (en
Inventor
Alexandre Forestier
Didier Hernandez
Eric Conete
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Safran Aircraft Engines SAS
Original Assignee
SNECMA Moteurs SA
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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 turbomachines and more particularly it relates to the interface between the high pressure turbine and the combustion chamber of turbojets having 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 room are made in a same material, usually of metal type.
  • HPT nozzle inlet distributor
  • the combustion chamber as well as the casing (also called envelope) of this room are made in a same material, usually of metal type.
  • CMC-type high temperature composite materials as shown in US-A-5,291,732.
  • difficulties of implementation of these materials and their cost make that their use is most often limited to the combustion chamber itself, the distributor inlet of the high pressure turbine and the remaining housing then made more typically in metallic materials.
  • 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, inlet of the high pressure turbine, and connection with the housing of the bedroom.
  • the present invention overcomes these disadvantages by proposing a connection crankcase with 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 whose manufacture is particularly easy.
  • a turbomachine comprising, in a envelope of metallic material and in a direction F of gas flow, a fuel injection assembly, combustion chamber made of material composite and a metal material distributor forming the entrance stage to vanes 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 resiliently secured by second removable attachment means.
  • the first removable fastening means are adapted to allow radial free expansion of said dispenser with respect to said envelope.
  • said second means of removable fasteners comprise on the one hand first holding means for pinch an end internal axial wall of said chamber of combustion between an internal circular platform of the dispenser and a flange supporting an inner annular wall of said envelope and second holding means for holding a wall with elastic prestressing external axial end of said combustion chamber on a platform external circular of the distributor.
  • the support flange is sectorised to compensate for the differences circumferential geometries resulting from the existing differential expansion at high temperatures between said inner circular distributor platform and said inner 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 made of metallic material held against this flange by said first removable fastening means.
  • said first removable fastening means have a plurality of bolts, each of which has screw axes running through a corresponding oblong hole of said support flange is provided with a shoulder on which is pressed against said ferrule so as to allow sliding of said support flange between said ferrule and said flange of the inner annular wall of the envelope.
  • said flange of the wall inner ring of the envelope has a circular groove for receiving a "omega" type circular sealing gasket intended to seal between said flange of the inner annular wall of the casing and said support flange.
  • a composite material shell advantageously brazed to said outer end wall of the combustion chamber is maintained with a elastic prestress against said external circular distributor platform by the second holding means, said ferrule having a groove to receive an omega-type circular seal intended for sealing between said outer end wall of the chamber of combustion and said outer circular platform of the dispenser.
  • this space 16 comprising, in the direction of gas flow, firstly an injection assembly formed of a plurality of injection systems 20 and regularly distributed around the duct 18 and each having a nozzle fuel injection device 22 fixed to the outer annular casing 12 (in a simplification of the drawings the mixer and the baffle associated with each injection nozzle were not shown), then a combustion chamber in high temperature composite material 24, CMC type or other (carbon by example), formed of an outer axial wall 26 and an inner axial wall 28, both coaxial axis 10, and a transverse wall 30 which constitutes the bottom of this combustion chamber and which has flaps 32, 34 fixed by all suitable means, for example metal or refractory bolts with screws conical), on the upstream ends 36, 38 of the axial walls 26, 28, this bottom of the chamber 30 being provided with orifices 40 to allow fuel injection and part of the oxidant in the combustion chamber 24, and finally a annular distributor 42 in metallic material forming an input stage of a high pressure turbine (not shown) and conventionally comprising a plurality of fixed vanes 44
  • the combustion chamber is mounted floating in the annular envelope and held in position by the only distributor to which it is resiliently secured by second removable attachment means which comprise on the one hand first holding means 52 for holding by pinching an end internal axial wall 54 of the combustion chamber (opposite the upstream end 38) between the inner circular platform of the distributor 48 and a flange 56 serving to support the inner annular envelope 14 and second holding means 58 for holding with prestressing elastic 60 an end outer axial wall 62 of said chamber of combustion (opposite the upstream end 36) on the outer circular platform of the dispenser 46.
  • the support flange 56 is mounted between a flange 64 of the inner annular casing 14 and a ferrule made of metallic material 66 held against this flange by the first removable fastening means 50.
  • Through orifices 68, 70 for the passage of the compressed oxidant previously separated, at the outlet of the diffusion duct 18, in at least two streams F1, F2 separate flowing from both sides of the combustion chamber 24 (and notably ensuring its cooling), are provided in the platforms external metal 46 and internal 48 of the distributor 42 to ensure a cooling the vanes fixed 44 of the distributor at the inlet of the rotor of the turbine high pressure.
  • the combustion chamber 24 having a coefficient of thermal expansion very different from other metal parts forming the turbomachine, in particular the dispenser 42 to which it is attached and the annular casing 12, 14, it is provided that the first removable fixing means 50 are adapted to allow at high temperatures radial free expansion of the dispenser with respect to the annular envelope.
  • the support flange 56 is pierced with holes oblongs 72 for cooperating with the screw axes of the plurality of bolts 50 a shoulder 74 serves to support the ferrule 66 so as to allow a sliding of this support flange between the ferrule and the flange 64 of the envelope 14.
  • this flange is sectorised to compensate for differences circumferential geometries resulting from the differential expansion existing at these high temperatures between the inner circular platform 48 of the dispenser and the internal axial wall 28, 54 of the combustion chamber.
  • the flange of the inner annular casing 64 comprises a circular groove 76 for receiving a circular seal of type "Omega" 78 for sealing between this flange of the envelope ring and the support flange 56.
  • the outer circular platform distributor 46 comprises a flange 80 provided with a circular groove 82 for receive a plate 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 outer circular platform of the distributor 46 also by means of a omega-type seal ring 86 mounted in a groove circular 88 of a shell of composite material 90, preferably brazed on the outer end wall of the combustion chamber 62, and maintained with an elastic prestress (obtained for example by the spring 60) against the platform external circular 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)

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 turbomachines and more particularly it relates to the interface between the high pressure turbine and the combustion chamber of turbojets having 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, comme le montre le brevet US-A-5 291 732. 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.Classically, 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 room are made in a same material, usually of metal type. However, in some special conditions of use using temperatures of significantly higher combustion, the use of a metal chamber is totally inappropriate thermal point of view and it must be resorted to a room based on CMC-type high temperature composite materials, as shown in US-A-5,291,732. difficulties of implementation of these materials and their cost make that their use is most often limited to the combustion chamber itself, the distributor inlet of the high pressure turbine and the remaining housing then made more typically in 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, inlet of the high pressure turbine, and connection with the housing 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 disadvantages by proposing a connection crankcase with 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 whose manufacture is particularly easy.

Ces buts sont atteints par une turbomachine comportant, dans une enveloppe en matériau métallique et selon un sens F d'écoulement des gaz, un ensemble d'injection d'un carburant, une chambre de combustion en matériau composite et un distributeur 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 goals are achieved by a turbomachine comprising, in a envelope of metallic material and in a direction F of gas flow, a fuel injection assembly, combustion chamber made of material composite and a metal material distributor forming the entrance stage to vanes 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 resiliently secured by second removable attachment 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 with the envelope, it significantly simplifies the manufacture of this chamber while particularly improving the sealing chamber-distributor. In addition, the perfect alignment of the vein that results in operation allows better feeding of the high pressure turbine. The removal of the usual flanges from the combustion chamber (for connection to the envelope) provides a significant gain in mass for this room and therefore 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 distributor on the room reporting the problems of relative displacement between the latter and the envelope at the level of the distributor, it is provided that the first removable fastening means are adapted to allow radial free expansion of said dispenser with respect 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 on the one hand first holding means for pinch an end internal axial wall of said chamber of combustion between an internal circular platform of the dispenser and a flange supporting an inner annular wall of said envelope and second holding means for holding a wall with elastic prestressing external axial 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 sectorised to compensate for the differences circumferential geometries resulting from the existing differential expansion at high temperatures between said inner circular distributor platform and said inner 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 made of metallic material held against this flange by said first removable fastening 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 fastening means have a plurality of bolts, each of which has screw axes running through a corresponding oblong hole of said support flange is provided with a shoulder on which is pressed against said ferrule so as to allow sliding of said support flange between said ferrule and said flange of the inner 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 ensure the tightness of the turbomachine, said flange of the wall inner ring of the envelope has a circular groove for receiving a "omega" type circular sealing gasket intended to seal between said flange of the inner annular wall of the casing and said support flange. Similarly, a composite material shell advantageously brazed to said outer end wall of the combustion chamber is maintained with a elastic prestress against said external circular distributor platform by the second holding means, said ferrule having a groove to receive an omega-type circular seal intended for sealing between said outer end wall of the chamber of combustion and said outer circular platform of the dispenser.

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 features and advantages of the present invention will emerge more clearly from the following description, given by way of non-limiting indication, with reference to the appended drawings in which:
  • FIG. 1 is a diagrammatic view in axial half-section of a central part of a turbomachine,
  • FIG. 2 is a detailed perspective view of the high-pressure turbine connection - combustion chamber at the level of the internal platform of the distributor,
  • FIG. 3 is a detailed perspective view of the high-pressure turbine connection - combustion chamber at the external platform of the distributor, and
  • Figure 4 is a view along line IV of Figure 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 interne) 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 rest of the description) comprising:
  • an envelope comprising an outer annular wall (or outer casing) 12 of metal material, of longitudinal axis 10, and an inner annular wall (or inner casing) coaxial 14 also made of metallic material,
  • an annular space 16 between the two annular walls 12, 14 of this envelope receiving the compressed oxidant, generally air, coming upstream of a compressor (not shown) of the turbomachine, through an annular duct 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 gas flow, firstly an injection assembly formed of a plurality of injection systems 20 and regularly distributed around the duct 18 and each having a nozzle fuel injection device 22 fixed to the outer annular casing 12 (in a simplification of the drawings the mixer and the baffle associated with each injection nozzle were not shown), then a combustion chamber in high temperature composite material 24, CMC type or other (carbon by example), formed of an outer axial wall 26 and an inner axial wall 28, both coaxial axis 10, and a transverse wall 30 which constitutes the bottom of this combustion chamber and which has flaps 32, 34 fixed by all suitable means, for example metal or refractory bolts with screws conical), on the upstream ends 36, 38 of the axial walls 26, 28, this bottom of the chamber 30 being provided with orifices 40 to allow fuel injection and part of the oxidant in the combustion chamber 24, and finally a annular distributor 42 in metallic material forming an input stage of a high pressure turbine (not shown) and conventionally comprising a plurality of fixed vanes 44 mounted between an outer circular platform 46 and a platform internal circular 48. The dispenser is based on support means 49 integral with the annular envelope of the turbomachine and is it 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 envelope and held in position by the only distributor to which it is resiliently secured by second removable attachment means which comprise on the one hand first holding means 52 for holding by pinching an end internal axial wall 54 of the combustion chamber (opposite the upstream end 38) between the inner circular platform of the distributor 48 and a flange 56 serving to support the inner annular envelope 14 and second holding means 58 for holding with prestressing elastic 60 an end outer axial wall 62 of said chamber of combustion (opposite the upstream end 36) on the outer circular platform of the dispenser 46. The support flange 56 is mounted between a flange 64 of the inner annular casing 14 and a ferrule made of metallic material 66 held against this flange by the first removable fastening 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.Through orifices 68, 70 for the passage of the compressed oxidant previously separated, at the outlet of the diffusion duct 18, in at least two streams F1, F2 separate flowing from both sides of the combustion chamber 24 (and notably ensuring its cooling), are provided in the platforms external metal 46 and internal 48 of the distributor 42 to ensure a cooling the vanes fixed 44 of the distributor at the inlet of the rotor of the turbine 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 other metal parts forming the turbomachine, in particular the dispenser 42 to which it is attached and the annular casing 12, 14, it is provided that the first removable fixing means 50 are adapted to allow at high temperatures radial free expansion of the dispenser with respect to the annular envelope. To do this, the support flange 56 is pierced with holes oblongs 72 for cooperating with the screw axes of the plurality of bolts 50 a shoulder 74 serves to support the ferrule 66 so as to allow a sliding of this support flange between the ferrule and the flange 64 of the envelope 14. In addition, this flange is sectorised to compensate for differences circumferential geometries resulting from the differential expansion existing at these high temperatures between the inner 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.In order to seal the flow of gas flow between the chamber and the turbine, the flange of the inner annular casing 64 comprises a circular groove 76 for receiving a circular seal of type "Omega" 78 for sealing between this flange of the envelope ring and the support flange 56. Thus, the compressed oxidant flow in from the compressor and surrounding the room by F2 can only join the turbine only through the orifices 70. Similarly, the outer circular platform distributor 46 comprises a flange 80 provided with a circular groove 82 for receive a plate 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 outer circular platform of the distributor 46 also by means of a omega-type seal ring 86 mounted in a groove circular 88 of a shell of composite material 90, preferably brazed on the outer end wall of the combustion chamber 62, and maintained with an elastic prestress (obtained for example by the spring 60) against the platform external circular distributor 46 by the second holding means 58.

Claims (9)

  1. A turbomachine comprising a shell (12, 14) of metal material containing along a gas flow direction F: a fuel injection assembly (20; 22), a combustion chamber of composite material (24), and a nozzle of metal material (42) forming the fixed-blade inlet stage (44) of a high pressure turbine, said nozzle being supported by said shell and being fixed thereto by first releasable fixing means (50), characterised in that said combustion chamber is mounted in floating manner inside said shell and is held in position solely by said nozzle to which it is fixed in resilient manner by second releasable fixing means (52, 58, 60).
  2. A turbomachine according to claim 1, characterised in that said first releasable fixing means are adapted to enable said nozzle to expand freely in a radial direction relative to said shell.
  3. A turbomachine according to claim 1, characterised in that said second releasable fixing means comprise firstly first holding means (52) for holding an inner axial wall (54) at the end of said combustion chamber clamped between an inner circular platform of the nozzle (48) and a flange (56) serving to support an inner annular wall (14) of said shell, and second holding means (58) for holding an outer axial wall (62) at the end of said combustion chamber with resilient prestress (60) against an outer circular platform of the nozzle (46).
  4. A turbomachine according to claim 3, characterised in that said support flange is subdivided into sectors to compensate for circumferential geometrical differences that result from the differential expansions that exist at high temperatures between said inner circular platform of the nozzle and said inner axial wall of the combustion chamber.
  5. A turbomachine according to claim 3, characterised in that said support flange is mounted between a flange (64) of said inner annular wall of the shell and a ring of metal material (66) held against said flange by said first releasable fixing means.
  6. A turbomachine according to claim 5, characterised in that said first releasable fixing means comprise a plurality of bolts (50) with the screw shanks thereof that pass through respective corresponding oblong holes (72) of said support flange being provided with respective shoulders (74) against which said ring is caused to bear so as to enable said support flange to slide between said ring and said flange of the inner annular wall of the shell.
  7. A turbomachine according to claim 6, characterised in that said flange of the inner annular wall of the shell has a circular groove (76) for receiving an omega type circular sealing gasket (78) for providing sealing between said flange of the inner annular wall of the shell and said support flange.
  8. A turbomachine according to claim 3, characterised in that it further comprises a composite material ring (90) advantageously brazed to said outer wall at the end of the combustion chamber and held with resilient prestress (60) against said outer circular platform of the nozzle by said second holding means.
  9. A turbomachine according to claim 8, characterised in that said ring has a circular groove (88) for receiving an omega type circular sealing gasket (86) for providing sealing between said outer wall at the end of the combustion chamber and said outer circular platform of the nozzle.
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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EP1265032A1 EP1265032A1 (en) 2002-12-11
EP1265032B1 true EP1265032B1 (en) 2004-10-06

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US (1) US6679062B2 (en)
EP (1) EP1265032B1 (en)
JP (1) JP3983603B2 (en)
DE (1) DE60201467T2 (en)
FR (1) FR2825780B1 (en)

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JP3983603B2 (en) 2007-09-26
FR2825780B1 (en) 2003-08-29
US20020184891A1 (en) 2002-12-12
US6679062B2 (en) 2004-01-20
DE60201467T2 (en) 2006-03-09
FR2825780A1 (en) 2002-12-13
JP2003035104A (en) 2003-02-07
DE60201467D1 (en) 2004-11-11
EP1265032A1 (en) 2002-12-11

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