EP1265031B1 - Fixing of metallic cowls on turbomachine combustion chamber liners made of CMC materials - Google Patents

Fixing of metallic cowls on turbomachine combustion chamber liners made of CMC materials Download PDF

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Publication number
EP1265031B1
EP1265031B1 EP02291360A EP02291360A EP1265031B1 EP 1265031 B1 EP1265031 B1 EP 1265031B1 EP 02291360 A EP02291360 A EP 02291360A EP 02291360 A EP02291360 A EP 02291360A EP 1265031 B1 EP1265031 B1 EP 1265031B1
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EP
European Patent Office
Prior art keywords
combustion chamber
axially
chamber according
wall
side walls
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EP02291360A
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German (de)
French (fr)
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EP1265031A1 (en
Inventor
Gwénaelle Calvez
Didier Hernandez
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Safran Aircraft Engines SAS
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SNECMA SAS
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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
    • F23R3/007—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
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2211/00—Thermal dilatation prevention or compensation

Definitions

  • the present invention relates to the specific field of turbomachines and is more particularly concerned with the problem posed by the mounting of a metal bottom of a combustion chamber of a turbomachine on the walls of composite material of the CMC type (ceramic matrix composite ) of this room.
  • the high pressure turbine including its inlet nozzle (HPT nozzle), the injection system, the combustion chamber and the casing (also called envelope) of this chamber are made in metallic type materials.
  • HPT nozzle inlet nozzle
  • the injection system the combustion chamber
  • the casing also called envelope
  • metallic type materials metallic type materials.
  • the use of an all-metal chamber is from a thermal point of view totally inadequate and it must be resorted to a chamber based on of high temperature composite materials of the CMC type.
  • these materials being very expensive and of low resistance to high mechanical stress, their use is most often limited to the combustion chamber itself and more particularly to its only axial walls, the inlet valve of the high pressure turbine, the injection system and the housing then remaining more typically made of metal materials.
  • the present invention overcomes these drawbacks by proposing a metal chamber bottom assembly having the capacity to absorb the displacements induced by the differences of the coefficients of expansion between this metallic background and the composite walls of the combustion chamber.
  • An object of the invention is also to provide a mounting having a good dynamic behavior and a good seal.
  • annular combustion chamber comprising outer and inner axial walls of composite material and a chamber bottom of metallic material, said chamber bottom being held in position on said outer and inner axial walls by fixing means, characterized in that said securing means traverses annular cavities for receiving end cylindrical portions of said outer and inner axial walls and created between peripheral edges of said chamber bottom and downstream facing return portions thereof, a determined clearance J between said peripheral edges and the opposite faces of said external and internal axial walls being provided so as to allow radial free expansion of said chamber bottom with respect to said axial walls in operation, said chamber bottom further comprising means to seal between said chamber bottom and said axial walls.
  • the fastening means are constituted by a plurality of bolts, preferably with a prison nut.
  • the outer and inner axial walls are provided with a plurality of holes intended to cooperate with said fixing means once these mounted on said chamber bottom.
  • the sealing means comprise a "slat" type circular seal mounted in a circular groove of said metal chamber bottom and intended to provide a support on said axial wall of the combustion chamber opposite.
  • said "slatted" circular seal comprises in its downstream part a spoiler intended to provide an O-bearing on said axial wall facing the combustion chamber. It must be sectored and it is held in abutment against said axial wall by means of an elastic element fixed on said metal chamber bottom. This elastic element is constituted by a leaf spring.
  • the chamber base can further incorporate inner and outer caps made of metallic material which extend its peripheral edges upstream and allow better control of the dynamic behavior.
  • the outer fairing (or cap) 34 extending upstream (with respect to the flow F) the outer wall 26 of the combustion chamber and the inner fairing (or cap) 36 extending towards the upstream (with respect to the flow F) the internal wall 28 of the combustion chamber are directly integrated in the chamber bottom 30 and are thus made of metal material (simplifying all the general shape of the upstream ends of the combustion chamber) which can therefore consist of simple cylindrical parts).
  • a configuration with a fairing (single pack single piece toric) connecting the two ends of the upstream walls of the combustion chamber (and then provided with openings for the passage of the injection nozzles 22) is also possible.
  • the metal annular bottom 30 of the combustion chamber which has a coefficient of thermal expansion very different from that of the external axial walls 26 and internal 28 of composite material of the combustion chamber, is held in position on the ends cylindrical upstream of the axial walls by a plurality of fastening means 38, 40 regularly distributed about the longitudinal axis 10.
  • These fastening means pass through annular cavities 42, 44, intended to receive the cylindrical end portions of these axial walls. , and created between peripheral edges of the chamber bottom 30 and return portions facing 46, 48 extending the caps 34, 36 downstream.
  • the fastening means 38, 40 are formed by a plurality of metal bolts of prison nut type, that is to say each comprising a screw 38a, a nut 38b and a stop cage 38c fixed on the chamber bottom 30 (advantageously by spot welding) and ensuring a locking in rotation of the nut.
  • the tightening (during assembly) is obtained directly by only screwing the screw without the need for the use of special tools for the immobilization in rotation of the nut (clamp for example), this being obtained very simply by the single stop cage.
  • disassembly can also be done very simply in reverse by simply loosening the screw.
  • a clearance J between the inner faces of the external axial walls 28 and inner 26 and the peripheral edges facing the chamber bottom 30 is calculated so as to allow in operation free expansion of the metal cap with respect to these axial walls of composite material .
  • This game makes it possible to absorb the dilatations of the chamber bottom without damaging the composite axial walls that move little radially.
  • the double-centering system of the outer and inner walls 28 and 28 in the corresponding cavities 42, 44 makes it possible to ensure relative sealing of the chamber bottom while also serving for axial retention during assembly (cold) as during flight phases. in cruising mode (hot).
  • FIG. 2 generally illustrates a second exemplary embodiment whose detail is shown in FIG. 2a and in which to guarantee a better seal between the external axial wall 26 or internal wall 28 and the chamber bottom 30, a circular seal of the type "Slats" 50, 52 is mounted in a circular groove 54, 56 made at the end of the downstream return portion 46, 48 of the outer cap 34 or inner 36.
  • This seal comprises in its downstream portion a spoiler 58, 60 for providing a toric support on the wall axial facing 26, 28 of the combustion chamber.
  • the seal is pressed against the wall by an elastic element 62, 64, preferably a leaf spring, and held in position by a plurality of pins 66, 68 secured to the downstream end of the cap.
  • the clearance between the peripheral edges of the chamber bottom and the inner faces of the axial walls is determined to allow the expansion of the chamber bottom to be absorbed without damaging the axial walls made of composite material.
  • the seal sealing with the outer axial wall is prestressed cold and the sealant with the inner wall is brought into contact only. Hot, it is the opposite because of the differences in expansion between the metal chamber bottom and the inner and outer walls.

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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)
  • Gasket Seals (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

Domaine de l'inventionField of the invention

La présente invention se rapporte au domaine spécifique des turbomachines et elle s'intéresse plus particulièrement au problème posé par le montage d'un fond métallique de chambre de combustion d'une turbomachine sur les parois en matériau composite de type CMC (composite à matrice céramique) de cette chambre.The present invention relates to the specific field of turbomachines and is more particularly concerned with the problem posed by the mounting of a metal bottom of a combustion chamber of a turbomachine on the walls of composite material of the CMC type (ceramic matrix composite ) of this room.

Art antérieurPrior art

Classiquement, dans un turboréacteur ou un turbopropulseur, la turbine haute pression, notamment son distributeur d'entrée (HPT nozzle), le système d'injection, la chambre de combustion ainsi que le carter (appelé aussi enveloppe) de cette chambre sont réalisés dans des matériaux de type métallique. Toutefois, dans certaines conditions particulières d'utilisation mettant en oeuvre des températures de combustion notablement élevées, l'emploi d'une chambre entièrement 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. Cependant, ces matériaux étant très coûteux et de faible résistance aux fortes sollicitations mécaniques, leur utilisation est le plus souvent limitée à la chambre de combustion elle même et plus particulièrement à ses seules parois axiales, le distributeur d'entrée de la turbine haute pression, le système d'injection 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 notamment au niveau de la liaison entre les parois en matériau composite de la chambre de combustion et le fond de chambre métallique. On connaît toutefois par la demande EP 1,152,191 une liaison de fond de chambre présentant une liberté de déplacement entre le fond en superalliage et les parois en matériau composite.Conventionally, in a turbojet or a turboprop, the high pressure turbine, including its inlet nozzle (HPT nozzle), the injection system, the combustion chamber and the casing (also called envelope) of this chamber are made in metallic type materials. However, under certain particular conditions of use involving significantly higher combustion temperatures, the use of an all-metal chamber is from a thermal point of view totally inadequate and it must be resorted to a chamber based on of high temperature composite materials of the CMC type. However, these materials being very expensive and of low resistance to high mechanical stress, their use is most often limited to the combustion chamber itself and more particularly to its only axial walls, the inlet valve of the high pressure turbine, the injection system and the housing then remaining more typically made of metal materials. However, metal materials and composite materials have very different coefficients of thermal expansion. This results in particularly acute problems especially at the level of the connection between the composite material walls of the combustion chamber and the metal chamber bottom. However, the demand is known EP 1,152,191 a chamber bottom connection having freedom of movement between the superalloy bottom and the walls of composite material.

Le brevet US 5 291 732 montre une chambre de combustion avec des parois en matériau composite dont la fixation au carter permet une libre dilatation axiale et radiale.The patent US 5,291,732 shows a combustion chamber with walls of composite material whose attachment to the housing allows free axial and radial expansion.

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

La présente invention pallie ces inconvénients en proposant un montage de fond de chambre métallique ayant la capacité d'absorber les déplacements induits par les différences des coefficients de dilatation entre ce fond métallique et les parois en composite de la chambre de combustion. Un but de l'invention est aussi de réaliser un montage ayant une bonne tenue dynamique et une bonne étanchéité.The present invention overcomes these drawbacks by proposing a metal chamber bottom assembly having the capacity to absorb the displacements induced by the differences of the coefficients of expansion between this metallic background and the composite walls of the combustion chamber. An object of the invention is also to provide a mounting having a good dynamic behavior and a good seal.

Ces buts sont atteints par une chambre de combustion annulaire comportant des parois axiales externe et interne en matériau composite et un fond de chambre en matériau métallique, ledit fond de chambre étant maintenu en position sur lesdites parois axiales externe et interne par des moyens de fixation, caractérisée en ce que lesdits moyens de fixation traversent des cavités annulaires destinées à recevoir des parties cylindriques d'extrémité desdites parois axiales externe et interne et créées entre des bords périphériques dudit fond de chambre et des parties en retour vers l'aval leur faisant face, un jeu déterminé J entre lesdits bords périphériques et les faces en regard desdites parois axiales externe et interne étant prévu de façon à permettre en fonctionnement une libre dilatation radiale dudit fond de chambre par rapport auxdites parois axiales, ledit fond de chambre comportant en outre des moyens pour assurer l'étanchéité entre ledit fond de chambre et lesdites parois axiales.These objects are achieved by an annular combustion chamber comprising outer and inner axial walls of composite material and a chamber bottom of metallic material, said chamber bottom being held in position on said outer and inner axial walls by fixing means, characterized in that said securing means traverses annular cavities for receiving end cylindrical portions of said outer and inner axial walls and created between peripheral edges of said chamber bottom and downstream facing return portions thereof, a determined clearance J between said peripheral edges and the opposite faces of said external and internal axial walls being provided so as to allow radial free expansion of said chamber bottom with respect to said axial walls in operation, said chamber bottom further comprising means to seal between said chamber bottom and said axial walls.

Avec ce système de fixation par simple boulonnage et montage coulissant, les dilatations du fond de chambre métallique sont absorbées sans détériorer les parois en matériau composite, tout en assurant une parfaite étanchéité à froid comme à chaud.With this system of fixing by simple bolting and sliding assembly, the expansions of the metal chamber bottom are absorbed without damaging the walls of composite material, while ensuring a perfect seal cold and hot.

Les moyens de fixation sont constitués par une pluralité de boulons, de préférence à écrou prisonnier.The fastening means are constituted by a plurality of bolts, preferably with a prison nut.

Avantageusement, les parois axiales externe et interne sont pourvues d'une pluralité de trous destinés à coopérer avec lesdits moyens de fixation une fois ceux-ci montés sur ledit fond de chambre.Advantageously, the outer and inner axial walls are provided with a plurality of holes intended to cooperate with said fixing means once these mounted on said chamber bottom.

De préférence, les moyens d'étanchéité comportent un joint circulaire de type « à lamelles » monté dans une gorge circulaire dudit fond de chambre métallique et destiné à assurer un appui sur ladite paroi axiale de la chambre de combustion en regard. De préférence, ledit joint circulaire « à lamelles » comporte dans sa partie aval un béquet destiné à assurer un appui torique sur ladite paroi axiale en regard de la chambre de combustion. Il doit être sectorisé et il est maintenu en appui contre ladite paroi axiale au moyen d'un élément élastique fixé sur ledit fond de chambre métallique. Cet élément élastique est constitué par un ressort à lames.Preferably, the sealing means comprise a "slat" type circular seal mounted in a circular groove of said metal chamber bottom and intended to provide a support on said axial wall of the combustion chamber opposite. Preferably, said "slatted" circular seal comprises in its downstream part a spoiler intended to provide an O-bearing on said axial wall facing the combustion chamber. It must be sectored and it is held in abutment against said axial wall by means of an elastic element fixed on said metal chamber bottom. This elastic element is constituted by a leaf spring.

Selon un mode de réalisation avantageux, le fond de chambre peut intégrer en outre des casquettes interne et externe en matériau métallique qui prolongent vers l'amont ses bords périphériques et permettent une meilleure maîtrise de la tenue dynamique.According to an advantageous embodiment, the chamber base can further incorporate inner and outer caps made of metallic material which extend its peripheral edges upstream and allow better control of the dynamic behavior.

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 d'injection d'une turbomachine incorporant un premier exemple de réalisation d'un assemblage selon l'invention,
  • la figure la montre un détail de l'assemblage de la figure 1,
  • la figure 2 est une vue schématique en demi-coupe axiale d'une partie d'injection d'une turbomachine incorporant un second exemple de réalisation d'un assemblage selon l'invention, et
  • la figure 2a montre un détail de l'assemblage de la figure 2.
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 schematic axial half-sectional view of an injection part of a turbomachine incorporating a first embodiment of an assembly according to the invention,
  • FIG. 1 shows a detail of the assembly of FIG. 1,
  • FIG. 2 is a schematic axial half-sectional view of an injection part of a turbomachine incorporating a second embodiment of an assembly according to the invention, and
  • Figure 2a shows a detail of the assembly of Figure 2.

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

Les figures 1 et 2 montrent en demi-coupe axiale une partie d'injection d'une turbomachine comprenant :

  • une enveloppe annulaire externe (ou carter externe) 12, d'axe longitudinal 10,
  • une enveloppe annulaire interne (ou carter interne) coaxiale 14,
  • un espace annulaire 16 compris entre les deux enveloppes 12 et 14 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 (on notera la présence de la grille de diffusion 18a) définissant un flux général F d'écoulement des gaz,
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 les mélangeur et déflecteur associés à chaque buse d'injection n'ont pas été représentés), ensuite une chambre de combustion annulaire 24, formée d'une paroi axiale externe 26 et d'une paroi axiale interne 28, toutes deux coaxiales d'axe 10 et réalisées en un matériau composite haute température, de type CMC ou autres (carbone par exemple), et d'une paroi transversale 30 réalisée en un matériau métallique, formant fond de chambre, et pourvue d'ouvertures 32 pour la fixation d'une partie du système d'injection, et enfin un distributeur annulaire (non représenté) formant un étage d'entrée d'une turbine haute pression.FIGS. 1 and 2 show, in axial half-section, an injection part of a turbomachine comprising:
  • an outer annular casing (or outer casing) 12, of longitudinal axis 10,
  • an inner annular envelope (or inner casing) coaxial 14,
  • an annular space 16 between the two envelopes 12 and 14 receiving the compressed oxidant, generally air, coming upstream of a compressor (not shown) of the turbomachine, through an annular diffusion duct 18 (on note the presence of the diffusion gate 18a) defining a general flow F of gas flow,
this space 16 comprising, in the direction of gas flow, first of all an injection assembly formed of a plurality of injection systems 20 regularly distributed around the duct 18 and each having a nozzle fuel injection 22 fixed on the outer annular casing 12 (for the sake of simplification of the drawings the mixer and baffle associated with each injection nozzle have not been shown), then an annular combustion chamber 24, formed an outer axial wall 26 and an inner axial wall 28, both coaxial with axis 10 and made of a high temperature composite material, of CMC or other type (carbon for example), and a transverse wall 30 made of a metallic material, forming chamber bottom, and provided with openings 32 for fixing a part of the injection system, and finally an annular distributor (not shown) forming an inlet stage of a high turbine pressure.

Dans les deux modes de réalisation illustrés, le carénage (ou casquette) externe 34 prolongeant vers l'amont (par rapport au flux F) la paroi externe 26 de la chambre de combustion et le carénage (ou casquette) interne 36 prolongeant vers l'amont (par rapport au flux F) la paroi interne 28 de la chambre de combustion sont directement intégrées au fond de chambre 30 et sont donc comme lui réalisés en matériau métallique (simplifiant d'autant la forme générale des extrémités amont de la chambre de combustion qui peuvent donc être constituées par de simples parties cylindriques). Bien entendu, une configuration avec un carénage (caquette unique monobloc de forme torique) reliant les deux extrémités des parois amont de la chambre de combustion (et muni alors d'ouvertures pour le passage des buses d'injection 22) est aussi envisageable.In the two embodiments shown, the outer fairing (or cap) 34 extending upstream (with respect to the flow F) the outer wall 26 of the combustion chamber and the inner fairing (or cap) 36 extending towards the upstream (with respect to the flow F) the internal wall 28 of the combustion chamber are directly integrated in the chamber bottom 30 and are thus made of metal material (simplifying all the general shape of the upstream ends of the combustion chamber) which can therefore consist of simple cylindrical parts). Of course, a configuration with a fairing (single pack single piece toric) connecting the two ends of the upstream walls of the combustion chamber (and then provided with openings for the passage of the injection nozzles 22) is also possible.

Selon l'invention, le fond annulaire métallique 30 de la chambre de combustion qui a un coefficient de dilatation thermique très différent de celui des parois axiales externe 26 et interne 28 en matériau composite de la chambre de combustion, est maintenu en position sur les extrémités cylindriques amont des parois axiales par une pluralité de moyens de fixation 38, 40 régulièrement répartis autour de l'axe longitudinal 10. Ces moyens de fixation traversent des cavités annulaires 42, 44, destinées à recevoir les parties cylindriques d'extrémité de ces parois axiales, et créées entre des bords périphériques du fond de chambre 30 et des parties en retour en regard 46, 48 prolongeant les casquettes 34, 36 vers l'aval.According to the invention, the metal annular bottom 30 of the combustion chamber which has a coefficient of thermal expansion very different from that of the external axial walls 26 and internal 28 of composite material of the combustion chamber, is held in position on the ends cylindrical upstream of the axial walls by a plurality of fastening means 38, 40 regularly distributed about the longitudinal axis 10. These fastening means pass through annular cavities 42, 44, intended to receive the cylindrical end portions of these axial walls. , and created between peripheral edges of the chamber bottom 30 and return portions facing 46, 48 extending the caps 34, 36 downstream.

Selon un premier exemple de réalisation, illustré de façon générale à la figure 1 et plus en détail à la figure 1A, les moyens de fixation 38, 40 sont formés par une pluralité de boulons métalliques de type à écrou prisonnier, c'est à dire comportant chacun une vis 38a, un écrou 38b et une cage d'arrêt 38c fixée sur le fond de chambre 30 (avantageusement par une soudure par point) et assurant un blocage en rotation de l'écrou. Avec ce type de boulons, le serrage (lors du montage) est obtenu directement par le seul vissage de la vis sans qu'il soit besoin de l'emploi d'un outillage particulier pour l'immobilisation en rotation de l'écrou (pince par exemple), celle-ci étant obtenue très simplement par la seule cage d'arrêt. De même, le démontage peut s'effectuer aussi très simplement de manière inverse par le seul desserrage de la vis.According to a first exemplary embodiment, generally illustrated in FIG. 1 and in more detail in FIG. 1A, the fastening means 38, 40 are formed by a plurality of metal bolts of prison nut type, that is to say each comprising a screw 38a, a nut 38b and a stop cage 38c fixed on the chamber bottom 30 (advantageously by spot welding) and ensuring a locking in rotation of the nut. With this type of bolts, the tightening (during assembly) is obtained directly by only screwing the screw without the need for the use of special tools for the immobilization in rotation of the nut (clamp for example), this being obtained very simply by the single stop cage. Similarly, disassembly can also be done very simply in reverse by simply loosening the screw.

Un jeu J entre les faces internes des parois axiales externe 28 et interne 26 et les bords périphériques en regard du fond de chambre 30 est calculé de façon à permettre en fonctionnement une libre dilatation de la casquette métallique par rapport à ces parois axiales en matériau composite. Ce jeu permet en effet d'absorber les dilatations du fond de chambre sans détériorer les parois axiales en composite qui se déplacent peu radialement. Le système de double centrage des parois externe 26 et interne 28 dans les cavités correspondantes 42, 44 permet d'assurer une étanchéité relative du fond de chambre tout en servant aussi au maintien axial lors du montage (à froid) comme lors des phases de vol en régime de croisière (à chaud).A clearance J between the inner faces of the external axial walls 28 and inner 26 and the peripheral edges facing the chamber bottom 30 is calculated so as to allow in operation free expansion of the metal cap with respect to these axial walls of composite material . This game makes it possible to absorb the dilatations of the chamber bottom without damaging the composite axial walls that move little radially. The double-centering system of the outer and inner walls 28 and 28 in the corresponding cavities 42, 44 makes it possible to ensure relative sealing of the chamber bottom while also serving for axial retention during assembly (cold) as during flight phases. in cruising mode (hot).

Pour faciliter le montage du fond de chambre sur les parois axiales, celles-ci sont pourvues de trous 26a, 28b destinés à recevoir des douilles 38d, 40d traversées par les axes de vis des moyens de fixation 38, 40 montés préalablement sur le fond de chambre, le contact permanent des vis avec la casquette 34, 36 limitant les risques de perte du couple de serrage lors de ce montage. Ces douilles sur lesquelles vont coulisser les parois axiales 26, 28 lors de la dilatation du fond de chambre 30 favorisent en outre le centrage et l'appui de ces parois axiales.To facilitate the mounting of the chamber bottom on the axial walls, they are provided with holes 26a, 28b for receiving bushings 38d, 40d traversed by the screw axes of the fixing means 38, 40 previously mounted on the bottom of chamber, the permanent contact of the screws with the cap 34, 36 limiting the risk of loss of the tightening torque during this assembly. These bushings on which slide the axial walls 26, 28 during the expansion of the chamber bottom 30 further promote the centering and support of these axial walls.

La figure 2 illustre de façon générale un second exemple de réalisation dont le détail est montré à la figure 2a et dans lequel pour garantir une meilleure étanchéité entre la paroi axiale externe 26 ou interne 28 et le fond de chambre 30, un joint circulaire de type « à lamelles » 50, 52 est monté dans une gorge circulaire 54, 56 pratiquée à l'extrémité de la partie en retour aval 46, 48 de la casquette externe 34 ou interne 36. Ce joint d'étanchéité comporte dans sa partie aval un béquet 58, 60 destiné à assurer un appui torique sur la paroi axiale en regard 26, 28 de la chambre de combustion. Le joint est plaqué contre la paroi par un élément élastique 62, 64, de préférence un ressort à lames, et maintenu en position par une pluralité de pions 66, 68 solidaires de l'extrémité aval de la casquette.FIG. 2 generally illustrates a second exemplary embodiment whose detail is shown in FIG. 2a and in which to guarantee a better seal between the external axial wall 26 or internal wall 28 and the chamber bottom 30, a circular seal of the type "Slats" 50, 52 is mounted in a circular groove 54, 56 made at the end of the downstream return portion 46, 48 of the outer cap 34 or inner 36. This seal comprises in its downstream portion a spoiler 58, 60 for providing a toric support on the wall axial facing 26, 28 of the combustion chamber. The seal is pressed against the wall by an elastic element 62, 64, preferably a leaf spring, and held in position by a plurality of pins 66, 68 secured to the downstream end of the cap.

On notera, comme précédemment, que le jeu existant entre les bords périphériques du fond de chambre et les faces internes des parois axiales est déterminé pour permettre d'absorber les dilatations du fond de chambre sans détériorer les parois axiales en matériau composite. Le joint assurant l'étanchéité avec la paroi axiale externe est précontraint à froid et celui assurant l'étanchéité avec la paroi interne est mis juste en contact. A chaud, c'est l'inverse du fait des différences de dilatation entre le fond de chambre métallique et les parois interne et externe.It will be noted, as previously, that the clearance between the peripheral edges of the chamber bottom and the inner faces of the axial walls is determined to allow the expansion of the chamber bottom to be absorbed without damaging the axial walls made of composite material. The seal sealing with the outer axial wall is prestressed cold and the sealant with the inner wall is brought into contact only. Hot, it is the opposite because of the differences in expansion between the metal chamber bottom and the inner and outer walls.

Claims (9)

  1. An annular combustion chamber including outer and inner axially-extending side walls (26, 28) of composite material and an end wall (30) of metal material, said end wall being held in position on said outer and inner side walls by fixing means (38, 40), the chamber being characterised in that said fixing means pass through annular cavities (42, 44) that are designed to receive cylindrical end portions of said outer and inner side walls, and that are created between peripheral edges of said end wall and facing portions (46, 48) folded downstream, a determined amount of clearance J being provided between said peripheral edges and the facing faces of said outer and inner side walls in such a manner as to allow expansion to take place freely, in operation, in a radial direction between said end wall and said axially-extending side walls, said end wall further comprising means (50-68) to ensure sealing between said end wall and axially-extending said side walls.
  2. A combustion chamber according to claim 1, characterised in that said fixing means are constituted by a plurality of bolts, preferably captive-nut bolts.
  3. A combustion chamber according to claim 1, characterised in that said outer and inner axially-extending side walls are provided with a plurality of holes (26a, 28b) designed to co-operate with said fixing means once said fixing means are mounted on said end wall.
  4. A combustion chamber according to claim 1, characterised in that said sealing means include a "spring blade" type circular gasket (50, 52) mounted in a circular groove (54, 56) of said metal end-wall and designed to bear on said facing axially-extending side wall of the facing combustion chamber.
  5. A combustion chamber according to claim 4, characterised in that, in its downstream portion, said "spring blade" circular gasket includes a rim (58, 60) designed to bear in toroidal manner on said facing axially-extending side wall of the combustion chamber.
  6. A combustion chamber according to claim 4, characterised in that said circular sealing gasket is divided into sectors.
  7. A combustion chamber according to claim 4, characterised in that said circular sealing gasket is held against said axially-extending side wall by means of a resilient element (62, 64) fixed on said metal end-wall.
  8. A combustion chamber according to claim 7, characterised in that said resilient element is constituted by a blade spring.
  9. A combustion chamber according to claim 1, characterised in that said end wall integrates inner and outer caps (34, 36) of metal material which extend its peripheral edges upstream.
EP02291360A 2001-06-06 2002-06-04 Fixing of metallic cowls on turbomachine combustion chamber liners made of CMC materials Expired - Lifetime EP1265031B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0107374A FR2825786B1 (en) 2001-06-06 2001-06-06 FIXING METAL CAPS ON TURBOMACHINE CMC COMBUSTION CHAMBER WALLS
FR0107374 2001-06-06

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EP1265031A1 EP1265031A1 (en) 2002-12-11
EP1265031B1 true EP1265031B1 (en) 2007-09-12

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EP02291360A Expired - Lifetime EP1265031B1 (en) 2001-06-06 2002-06-04 Fixing of metallic cowls on turbomachine combustion chamber liners made of CMC materials

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US (1) US6655148B2 (en)
EP (1) EP1265031B1 (en)
JP (1) JP3984104B2 (en)
DE (1) DE60222324T2 (en)
FR (1) FR2825786B1 (en)

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US20020184886A1 (en) 2002-12-12
FR2825786B1 (en) 2003-10-17
DE60222324T2 (en) 2008-06-12
JP2003021335A (en) 2003-01-24
US6655148B2 (en) 2003-12-02
EP1265031A1 (en) 2002-12-11
FR2825786A1 (en) 2002-12-13
DE60222324D1 (en) 2007-10-25
JP3984104B2 (en) 2007-10-03

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