EP1265031A1 - 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
EP1265031A1
EP1265031A1 EP02291360A EP02291360A EP1265031A1 EP 1265031 A1 EP1265031 A1 EP 1265031A1 EP 02291360 A EP02291360 A EP 02291360A EP 02291360 A EP02291360 A EP 02291360A EP 1265031 A1 EP1265031 A1 EP 1265031A1
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EP
European Patent Office
Prior art keywords
combustion chamber
walls
axial
external
internal
Prior art date
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Granted
Application number
EP02291360A
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German (de)
French (fr)
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EP1265031B1 (en
Inventor
Gwénaelle Calvez
Didier Hernandez
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Safran Aircraft Engines SAS
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SNECMA Moteurs SA
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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 turbomachinery and it is more particularly interested in the problem posed by the mounting of a metal bottom of the combustion chamber of a turbomachine on walls made of CMC type composite material (ceramic matrix composite) from this room.
  • the turbine high pressure including its inlet distributor (HPT nozzle), the system the combustion chamber as well as the casing (also called casing) of this chamber are made of metallic type materials.
  • HPT nozzle inlet distributor
  • the system the combustion chamber as well as the casing (also called casing) of this chamber are made of metallic type materials.
  • the use of a chamber entirely metallic proves from a thermal point of view totally unsuitable and it must be resorted to a chamber made from high composite materials CMC type temperature.
  • 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 distributor of the high pressure turbine, the injection system and the remaining casing then produced more conventionally in metallic materials.
  • Gold, metallic materials and composite materials have very different coefficients of thermal expansion. This results in particularly acute problems, particularly with regard to the connection between composite material walls of the combustion chamber and the chamber bottom metallic.
  • the present invention overcomes these drawbacks by proposing an assembly of metal chamber bottom capable of absorbing induced displacements by the differences in the expansion coefficients between this metallic background and the composite walls of the combustion chamber.
  • An object of the invention is also to produce an assembly having good dynamic strength and good sealing.
  • annular combustion chamber comprising external and internal axial walls of composite material and a chamber bottom of metallic material, said chamber bottom being held in position on said external external and internal walls by fixing means, characterized in that said fixing means pass through annular cavities intended to receive cylindrical end portions of said external and internal axial walls and created between peripheral edges of said chamber bottom and backward facing parts facing them, a determined clearance J between said peripheral edges and the facing faces of said external and internal axial walls being provided so as to allow in operation a free radial expansion of said chamber bottom relative to said axial walls.
  • the fixing means consist of a plurality of bolts, of preferably with captive nut.
  • the external and internal axial walls are provided with a plurality of holes intended to cooperate with said fixing means once these mounted on said chamber bottom.
  • this chamber bottom can further include means for sealing between said bottom of chamber and said axial walls.
  • These sealing means include a seal circular type "lamellae" mounted in a circular groove of said bottom metal chamber and intended to ensure support on said axial wall of the combustion chamber opposite.
  • said circular joint "to slats” has in its downstream part a spoiler intended to provide support O-ring on said axial wall opposite the combustion chamber. He must be segmented and it is kept in abutment against said axial wall by means of a elastic element fixed on said metal chamber bottom. This elastic element consists of a leaf spring.
  • the chamber bottom can integrate in addition internal and external metallic material caps which extend upstream its peripheral edges and allow better control of the dynamic outfit.
  • the fairing (or cap) outer 34 extending upstream (relative to the flow F) the outer wall 26 of the combustion chamber and the internal fairing (or cap) 36 extending upstream (relative to flow F) the internal wall 28 of the combustion are directly integrated into the bottom of the chamber 30 and are therefore made of metallic material (thereby simplifying the general shape of the upstream ends of the combustion chamber which can therefore be formed by simple cylindrical parts).
  • a configuration with a fairing (single monobloc cap in toric shape) connecting the two ends upstream walls of the combustion chamber (and then provided with openings for the passage of the injection nozzles 22) is also possible.
  • the metallic annular bottom 30 of the combustion which has a coefficient of thermal expansion very different from that of external axial 26 and internal 28 walls made of composite material of the combustion, is kept in position on the upstream cylindrical ends of the axial walls by a plurality of fixing means 38, 40 regularly distributed around the longitudinal axis 10.
  • These fixing 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 opposite parts 46, 48 extending the caps 34, 36 towards downstream.
  • the fixing means 38, 40 are formed by a plurality of metal bolts of the captive nut type, i.e. 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 rotation lock of the nut.
  • the tightening when mounting
  • the screw is obtained directly by simply screwing in the screw without the need for the use of special tools for immobilizing the nut in rotation (pliers for example), this being obtained very simply by the single cage Stop.
  • disassembly can also be done very simply so reverse by simply loosening the screw.
  • a clearance J between the internal faces of the external axial 28 and internal 26 walls and the peripheral edges opposite the chamber bottom 30 is calculated so as to allow in operation a free expansion of the metal cap relative to these axial walls of composite material .
  • This play in fact makes it possible to absorb the expansions of the chamber bottom without damaging the axial composite walls which move little radially.
  • the system of double centering of the external 26 and internal 28 walls in the corresponding cavities 42, 44 makes it possible to ensure a relative tightness of the chamber bottom while also serving for the axial maintenance during mounting (cold) as during the flight phases. at cruising speed (hot).
  • these are provided with holes 26a, 28b intended to receive sockets 38d, 40d crossed by the screw axes of the fixing means 38, 40 previously mounted on the chamber bottom, the permanent contact of the screws with the cap 34, 36 limiting the risk of losing the tightening torque during this assembly.
  • These sockets on which the axial walls 26, 28 will slide when the bottom expands chamber 30 further promote the centering and support of these axial walls.
  • FIG. 2 generally illustrates a second embodiment example the detail of which is shown in Figure 2a and in which to ensure better sealing between the external axial wall 26 or internal wall 28 and the chamber bottom 30, a “lamellar” type circular seal 50, 52 is mounted in a circular groove 54, 56 made at the end of the downstream return part 46, 48 of the cap external 34 or internal 36.
  • This seal comprises in its downstream part a spoiler 58, 60 intended to ensure an O-ring support on the opposite axial wall 26, 28 of the combustion chamber.
  • the seal is pressed against the wall by an element elastic 62, 64, preferably a leaf spring, and held in position by a plurality of pins 66, 68 integral with the downstream end of the cap.

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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)

Abstract

The combustion chamber for an aircraft gas turbine engine has inner (28) and outer (26) composite walls and a metal base (30) held in position by the walls. The base fixings extend across annular cavities (42,44) which receive the cylindrical sections of the ends of the walls. This defines a play between the peripheral edges of the base and the returned sections (46,48) and the opposing surfaces of the walls. This allows a radial expansion of the chamber base with respect to the walls.

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 turbomachinery and it is more particularly interested in the problem posed by the mounting of a metal bottom of the combustion chamber of a turbomachine on walls made of CMC type composite material (ceramic matrix composite) from 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.Conventionally, in a turbojet or a turboprop, the turbine high pressure, including its inlet distributor (HPT nozzle), the system the combustion chamber as well as the casing (also called casing) of this chamber are made of metallic type materials. However, under certain specific conditions of use using notably high combustion temperatures, the use of a chamber entirely metallic proves from a thermal point of view totally unsuitable and it must be resorted to a chamber made from high composite materials CMC type temperature. 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 distributor of the high pressure turbine, the injection system and the remaining casing then produced more conventionally in metallic materials. Gold, metallic materials and composite materials have very different coefficients of thermal expansion. This results in particularly acute problems, particularly with regard to the connection between composite material walls of the combustion chamber and the chamber bottom metallic.

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 an assembly of metal chamber bottom capable of absorbing induced displacements by the differences in the expansion coefficients between this metallic background and the composite walls of the combustion chamber. An object of the invention is also to produce an assembly having good dynamic strength and good sealing.

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.These aims are achieved by an annular combustion chamber comprising external and internal axial walls of composite material and a chamber bottom of metallic material, said chamber bottom being held in position on said external external and internal walls by fixing means, characterized in that said fixing means pass through annular cavities intended to receive cylindrical end portions of said external and internal axial walls and created between peripheral edges of said chamber bottom and backward facing parts facing them, a determined clearance J between said peripheral edges and the facing faces of said external and internal axial walls being provided so as to allow in operation a free radial expansion of said chamber bottom relative to 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.With this simple bolting and sliding mounting system, the dilations of the metal chamber bottom are absorbed without damaging the composite material walls.

Les moyens de fixation sont constitués par une pluralité de boulons, de préférence à écrou prisonnier.The fixing means consist of a plurality of bolts, of preferably with captive 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 external and internal axial walls are provided with a plurality of holes intended to cooperate with said fixing means once these mounted on said chamber bottom.

Selon un mode de réalisation préférentiel, ce fond de chambre peut comporter en outre des moyens pour assurer l'étanchéité entre ledit fond de chambre et lesdites parois axiales. Ces 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. According to a preferred embodiment, this chamber bottom can further include means for sealing between said bottom of chamber and said axial walls. These sealing means include a seal circular type "lamellae" mounted in a circular groove of said bottom metal chamber and intended to ensure support on said axial wall of the combustion chamber opposite. Preferably, said circular joint "to slats "has in its downstream part a spoiler intended to provide support O-ring on said axial wall opposite the combustion chamber. He must be segmented and it is kept in abutment against said axial wall by means of a elastic element fixed on said metal chamber bottom. This elastic element consists of 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 maítrise de la tenue dynamique.According to an advantageous embodiment, the chamber bottom can integrate in addition internal and external metallic material caps which extend upstream its peripheral edges and allow better control of the dynamic outfit.

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 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 an injection part of a turbomachine incorporating a first embodiment of an assembly according to the invention,
  • FIG. 1a shows a detail of the assembly of FIG. 1,
  • FIG. 2 is a schematic view in axial half-section of an injection part of a turbomachine incorporating a second embodiment of an assembly according to the invention, and
  • FIG. 2a shows a detail of the assembly of FIG. 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.Figures 1 and 2 show in axial half-section an injection portion of a turbomachine comprising
  • an external annular envelope (or external casing) 12, of longitudinal axis 10,
  • a coaxial internal annular envelope (or internal casing) 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 grid 18a) defining a general flow F of gas flow,
this space 16 comprising, in the direction of flow of the gases, first of all an injection assembly formed of a plurality of injection systems 20 regularly distributed around the conduit 18 and each comprising a fuel injection nozzle 22 fixed to the outer annular casing 12 (for the sake of simplification of the drawings the mixer and deflector associated with each injection nozzle have not been shown), then an annular combustion chamber 24, formed of an axial wall external 26 and an internal axial wall 28, both coaxial with axis 10 and made of a high temperature composite material, of the CMC or other type (carbon for example), and a transverse wall 30 made of a metallic material , forming the chamber bottom, and provided with openings 32 for fixing part of the injection system, and finally an annular distributor (not shown) forming an inlet stage of a high pressure turbine.

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 illustrated embodiments, the fairing (or cap) outer 34 extending upstream (relative to the flow F) the outer wall 26 of the combustion chamber and the internal fairing (or cap) 36 extending upstream (relative to flow F) the internal wall 28 of the combustion are directly integrated into the bottom of the chamber 30 and are therefore made of metallic material (thereby simplifying the general shape of the upstream ends of the combustion chamber which can therefore be formed by simple cylindrical parts). Of course, a configuration with a fairing (single monobloc cap in toric shape) connecting the two ends 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 metallic annular bottom 30 of the combustion which has a coefficient of thermal expansion very different from that of external axial 26 and internal 28 walls made of composite material of the combustion, is kept in position on the upstream cylindrical ends of the axial walls by a plurality of fixing means 38, 40 regularly distributed around the longitudinal axis 10. These fixing 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 opposite parts 46, 48 extending the caps 34, 36 towards 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, illustrated generally in the Figure 1 and in more detail in Figure 1A, the fixing means 38, 40 are formed by a plurality of metal bolts of the captive nut type, i.e. 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 rotation lock of the nut. With this type of bolt, the tightening (when mounting) is obtained directly by simply screwing in the screw without the need for the use of special tools for immobilizing the nut in rotation (pliers for example), this being obtained very simply by the single cage Stop. Similarly, disassembly can also be done very simply so 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 internal faces of the external axial 28 and internal 26 walls and the peripheral edges opposite the chamber bottom 30 is calculated so as to allow in operation a free expansion of the metal cap relative to these axial walls of composite material . This play in fact makes it possible to absorb the expansions of the chamber bottom without damaging the axial composite walls which move little radially. The system of double centering of the external 26 and internal 28 walls in the corresponding cavities 42, 44 makes it possible to ensure a relative tightness of the chamber bottom while also serving for the axial maintenance during mounting (cold) as during the flight phases. at cruising speed (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 mounting of the chamber bottom on the axial walls, these are provided with holes 26a, 28b intended to receive sockets 38d, 40d crossed by the screw axes of the fixing means 38, 40 previously mounted on the chamber bottom, the permanent contact of the screws with the cap 34, 36 limiting the risk of losing the tightening torque during this assembly. These sockets on which the axial walls 26, 28 will slide when the bottom expands chamber 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 embodiment example the detail of which is shown in Figure 2a and in which to ensure better sealing between the external axial wall 26 or internal wall 28 and the chamber bottom 30, a “lamellar” type circular seal 50, 52 is mounted in a circular groove 54, 56 made at the end of the downstream return part 46, 48 of the cap external 34 or internal 36. This seal comprises in its downstream part a spoiler 58, 60 intended to ensure an O-ring support on the opposite axial wall 26, 28 of the combustion chamber. The seal is pressed against the wall by an element elastic 62, 64, preferably a leaf spring, and held in position by a plurality of pins 66, 68 integral with 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 before, that the play existing between the edges chamber bottom peripherals and the inner faces of the axial walls is determined to allow the expansion of the chamber bottom to be absorbed without deteriorate the axial walls of composite material. The seal ensuring the tightness with the external axial wall is prestressed cold and the one ensuring the sealing with the inner wall is just brought into contact. When hot, it is the opposite due to the differences in expansion between the metal chamber bottom and the internal walls and external.

Claims (10)

Chambre de combustion annulaire comportant des parois axiales externe (26) et interne (28) en matériau composite et un fond de chambre (30) en matériau métallique, ledit fond de chambre étant maintenu en position sur lesdites parois axiales externe et interne par des moyens de fixation (38, 40), caractérisée en ce que lesdits moyens de fixation traversent des cavités annulaires (42, 44) 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 (46, 48) 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.Annular combustion chamber comprising external (26) and internal (28) axial walls of composite material and a chamber bottom (30) of metallic material, said chamber bottom being held in position on said external and internal axial walls by means fixing (38, 40), characterized in that said fixing means pass through annular cavities (42, 44) intended to receive cylindrical end portions of said axial external and internal walls and created between peripheral edges of said chamber bottom and parts facing downstream (46, 48) facing them, a determined clearance J between said peripheral edges and the facing faces of said external and internal axial walls being provided so as to allow in operation a free radial expansion of said chamber bottom with respect to said axial walls. Chambre de combustion selon la revendication 1, caractérisée en ce que lesdits moyens de fixation sont constitués par une pluralité de boulons, de préférence à écrou prisonnier.Combustion chamber according to claim 1, characterized in that the said fixing means consist of a plurality of bolts, preferably with captive nut. Chambre de combustion selon la revendication 1, caractérisée en ce que lesdites parois axiales externe et interne sont pourvues d'une pluralité de trous (26a, 28b) destinés à coopérer avec lesdits moyens de fixation une fois ceux-ci montés sur ledit fond de chambre.Combustion chamber according to claim 1, characterized in that said external and internal axial walls are provided with a plurality of holes (26a, 28b) intended to cooperate with said fixing means once these have been mounted on said chamber bottom . Chambre de combustion selon la revendication 1, caractérisée en ce que ledit fond de chambre comporte en outre des moyens (50-68) pour assurer l'étanchéité entre ledit fond de chambre et lesdites parois axiales.Combustion chamber according to claim 1, characterized in that said chamber bottom also comprises means (50-68) for sealing between said chamber bottom and said axial walls. Chambre de combustion selon la revendication 4, caractérisée en ce que lesdits moyens d'étanchéité comportent un joint circulaire de type « à lamelles » (50, 52) monté dans une gorge circulaire (54, 56) dudit fond de chambre métallique et destiné à assurer un appui sur ladite paroi axiale en regard de la chambre de combustion en regard.Combustion chamber according to Claim 4, characterized in that the said sealing means comprise a circular seal of the "lamella" type (50, 52) mounted in a circular groove (54, 56) of the said bottom of the metal chamber and intended to provide support on said axial wall facing the opposite combustion chamber. Chambre de combustion selon la revendication 5, caractérisée en ce que ledit joint circulaire « à lamelles » comporte dans sa partie aval un béquet (58, 60) destiné à assurer un appui torique sur ladite paroi axiale en regard de la chambre de combustion. Combustion chamber according to claim 5, characterized in that said circular "lamellar" seal comprises in its downstream part a spoiler (58, 60) intended to provide a toric support on said axial wall opposite the combustion chamber. Chambre de combustion selon la revendication 5, caractérisée en ce que ledit joint circulaire d'étanchéité est sectorisé.Combustion chamber according to claim 5, characterized in that said circular seal is sectorized. Chambre de combustion selon la revendication 5, caractérisée en ce que ledit joint circulaire d'étanchéité est maintenu en appui contre ladite paroi axiale au moyen d'un élément élastique (62, 64) fixé sur ledit fond de chambre métallique.Combustion chamber according to Claim 5, characterized in that the said circular gasket is held in abutment against the said axial wall by means of an elastic element (62, 64) fixed on the said bottom of the metallic chamber. Chambre de combustion selon la revendication 8, caractérisée en ce que ledit élément élastique est constitué par un ressort à lames.Combustion chamber according to claim 8, characterized in that said elastic element consists of a leaf spring. Chambre de combustion selon la revendication 1, caractérisée en ce que ledit fond de chambre intègre des casquettes interne et externe en matériau métallique (34, 36) qui prolongent vers l'amont ses bords périphériques.Combustion chamber according to claim 1, characterized in that said chamber bottom incorporates internal and external caps made of metallic material (34, 36) 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)

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FR0107374 2001-06-06
FR0107374A FR2825786B1 (en) 2001-06-06 2001-06-06 FIXING METAL CAPS ON TURBOMACHINE CMC COMBUSTION CHAMBER WALLS

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FR2896575A1 (en) * 2006-01-26 2007-07-27 Snecma Sa Annular combustion chamber for e.g. turbo propeller, has chamber base arranged between inner and outer walls in region that is provided upstream to chamber, where chamber base and walls are made of ceramic material
FR2905166A1 (en) * 2006-08-28 2008-02-29 Snecma Sa Annular combustion chamber for e.g. turboreactor, has cooling channel made between inner and outer fixation edges of chamber base and upstream fixation edges of inner and outer walls, where channel opens inside chamber
US8387395B2 (en) 2006-08-28 2013-03-05 Snecma Annular combustion chamber for a turbomachine
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Also Published As

Publication number Publication date
JP3984104B2 (en) 2007-10-03
DE60222324D1 (en) 2007-10-25
FR2825786B1 (en) 2003-10-17
FR2825786A1 (en) 2002-12-13
DE60222324T2 (en) 2008-06-12
US6655148B2 (en) 2003-12-02
US20020184886A1 (en) 2002-12-12
JP2003021335A (en) 2003-01-24
EP1265031B1 (en) 2007-09-12

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