EP1265035B1 - Double mounting of a ceramic matrix composite combustion chamber - Google Patents

Double mounting of a ceramic matrix composite combustion chamber Download PDF

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Publication number
EP1265035B1
EP1265035B1 EP02291364A EP02291364A EP1265035B1 EP 1265035 B1 EP1265035 B1 EP 1265035B1 EP 02291364 A EP02291364 A EP 02291364A EP 02291364 A EP02291364 A EP 02291364A EP 1265035 B1 EP1265035 B1 EP 1265035B1
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EP
European Patent Office
Prior art keywords
metal
combustion chamber
turbomachine according
tabs
composite material
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EP02291364A
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German (de)
French (fr)
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EP1265035A1 (en
Inventor
Didier Hernandez
Gwénaelle Calvez
Alexandre Forestier
Eric Conete
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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
    • F23R3/42—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
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2230/00—Manufacture
    • F05B2230/60—Assembly methods
    • F05B2230/604—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins
    • F05B2230/606—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins using maintaining alignment while permitting differential dilatation

Definitions

  • the present invention relates to the specific field of turbomachines and is more particularly concerned with the problem of mounting a combustion chamber made of a composite material of the CMC (ceramic matrix composite) type in the metal casing of a turbomachine.
  • CMC ceramic matrix composite
  • the high pressure turbine including its inlet nozzle (HPT nozzle), the combustion chamber and the casing (or envelope) of this chamber are made of the same material, generally of the type metallic.
  • HPT nozzle inlet nozzle
  • the combustion chamber and the casing (or envelope) of this chamber are made of the same material, generally of the type metallic.
  • the use of a metal chamber is from a thermal point of view totally inadequate and it must be resorted to a chamber based on CMC type high temperature composite materials.
  • the difficulties of implementation and the cost of these materials mean that their use is most often limited to the combustion chamber itself, the inlet valve of the high pressure turbine and the casing then remaining more conventionally achieved.
  • metallic materials metal materials and composite materials have very different coefficients of thermal expansion. This results in particularly acute problems of connection with the housing and the combustion chamber and sealing at the distributor at the inlet of the high pressure turbine.
  • the US Patent 6,131,384 shows a turbomachine according to this prior art.
  • the present invention overcomes these disadvantages by proposing a mounting of the combustion chamber in the casing having the capacity to absorb the displacements induced by the differences in the expansion coefficients of these parts.
  • a turbomachine comprising, in an envelope of metallic material and in a direction F of gas flow, a fuel injection system, a composite material combustion chamber having a longitudinal axis, and a metal material distributor forming the fixed blade inlet stage of a high pressure turbine, characterized in that said composite material combustion chamber is held in position in said metal casing by a plurality of flexible metal tabs having first and second ends, said first ends being interconnected by a metal flange crown fixed to said metal shell by first fixing means and said second ends being each fixed jointly by second fixing means on the one hand to said chamber of composite material combustion and secondly at one end of a composite material wall whose other end forms a support plane for a sealing element integral with said distributor and ensuring the sealing of the gas stream between said combustion chamber and said distributor, the flexibility of said fixing lugs permitting at high temperatures radial free expansion of said combustion chamber made of composite material with respect to said metal casing.
  • the first and second fastening means are preferably constituted by a plurality of bolts.
  • the second fixing means can also be constituted by crimping elements.
  • said sealing element is of the type "circular seal”. It may comprise a plurality of calibrated leakage orifices.
  • said metal ring interconnecting said first ends of said flexible metal tabs is mounted between connecting flanges of these two parts.
  • said metal ring may be fixed directly to said annular casing by conventional fastening means.
  • said first ends of the fixing lugs may either be fixed by brazing (or welding) to said metal flange ring or form a single piece with this metal ring.
  • the distributor is fixed on a downstream portion 14b of the inner annular envelope of the turbomachine by first removable fastening means preferably constituted by a plurality of bolts 50 while resting on support means 49 integral with the outer annular envelope of the turbomachine.
  • Through-holes 54, 56 formed in the outer metal 46 and inner 48 metal platforms of the distributor 42 are furthermore provided for cooling the vanes 44 of the distributor at the inlet of the rotor of the high-pressure turbine from the oxidant compressed available at the outlet of the diffusion duct 18 and flowing in two flows F1, F2 on either side of the combustion chamber 24.
  • These attachment tabs are mounted for a first part of them (see the tab referenced 58) between the outer annular casing 12a, 12b and the outer axial wall 26 of the combustion chamber and for a second part (such as the tab 60) between the inner annular envelope 14a, 14b and the inner axial wall 28 of the combustion chamber.
  • the number of legs may, for example, be in number equal to that of the injection nozzles or equal to a multiple of this number.
  • Each flexible fastening clip of metal material which can have a substantially triangular shape as illustrated Figure 1A , or consist of a single blade (not shown constant width or not), is welded or soldered by a first end 62; 64 to a metal ring 66a, 66b forming a flange and secured integrally by first fixing means 52; 68 to one or the other (depending on its location) of the outer or inner metal annular envelopes.
  • This attachment flange is intended to facilitate the maintenance of these legs on the metal shells.
  • these tabs and the metal ring together form a single piece of metal in one piece.
  • this tab is fixed jointly by second fixing means 74, 76 on the one hand at a downstream end 88; 90 of the external axial walls 26 and inner 28 of the combustion chamber made of ceramic composite material and secondly at one end of a ceramic composite wall 78a; 78b disposed in the extension of each of the outer and inner axial walls, forming a kind of a second chamber portion, and the other end forms a support plane for a sealing element integral with the distributor and sealing the gas stream between the combustion chamber 24 and the distributor 42.
  • connection of the second ends of the tabs 70, 72 with the downstream ends of the walls of the combustion chamber and the first ends of the ceramic composite walls forming the second chamber portion is carried out by a simple bolting, preferably of prison nut type to facilitate a possible assembly / disassembly and correlatively limit the dimensions of the legs.
  • the metal ring 66a, 66b interconnecting the first ends 62, 64 of the tabs is in turn preferably taken between existing connecting flanges between the upstream portions 12a, 14a and downstream 12b, 14b of the inner and outer annular envelopes and maintained fixedly by the first attachment means 52, 68 which are preferably also bolt type.
  • washers ceramic composite material 74a; 76a to allow to "drown" the conical heads of the screws of the bolts forming the second attachment means 74; 76.
  • the tightness of the gas stream between the combustion chamber 24 and the distributor 42 is provided by a "flap" circular seal 80, 82 mounted in a groove 84, 86 of each of the outer 46 and inner 48 platforms. dispenser and which bears directly on the second end portion of the ceramic composite wall 78a; 78b forming a support plane for this seal circular sealing.
  • the seal is held in abutment against this second end of the composite wall by means of a resilient element, leaf spring type 92, 94, fixed on the distributor.
  • an omega-type circular seal 96 mounted in a circular groove 98 of a flange of the inner annular casing 14 in direct contact with the inner circular platform 48 of the distributor and secondly by another "flap" circular seal 100 mounted in a circular groove 102 of the outer circular platform of the distributor 46 and one end is in direct contact with a circular spoiler 104 of the downstream portion 12b of the outer annular envelope.
  • Figure 1B illustrates a first variant of the previous embodiment in which the attachment of the tabs (only the case of the tab 60 is illustrated) at the downstream end 90 of the combustion chamber 24 is performed by a crimped connection, the bolts 76 being replaced by crimping elements 76b.
  • the cooling being able to take place through the crimping elements, it is no longer necessary to provide calibrated orifices at the lamellae joints 80, 82.
  • the metal ring 66a forming a flange interconnecting by brazing (or welding) the first ends 62 of the fastening tabs 58 of the outer axial wall of the combustion chamber 26 is no longer mounted between flanges but itself brazed (or welded) ) at a polarizer 106 centered and resting on the outer annular casing 12.
  • the metal ring 66b forming a flange interconnecting by brazing (or welding) the first ends 64 of the fixing lugs 60 of the inner axial wall of the combustion chamber 28 is no longer mounted between flanges but simply fixed directly to the inner annular casing 14 by conventional fastening means 108, for example of the bolt type.
  • the flexibility of the fixing lugs makes it possible to withstand the thermal expansion gap occurring at the temperatures elevated between the composite material combustion chamber and the metal annular envelopes while ensuring the maintenance and positioning of the chamber.

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'une chambre de combustion en matériau composite de type CMC (composite à matrice céramique) dans le carter métallique d'une turbomachine.The present invention relates to the specific field of turbomachines and is more particularly concerned with the problem of mounting a combustion chamber made of a composite material of the CMC (ceramic matrix composite) type in the metal casing of a turbomachine.

Art antérieurPrior art

Classiquement, dans un turboréacteur ou un turbopropulseur, la turbine haute pression, notamment son distributeur d'entrée (HPT nozzle), la chambre de combustion ainsi que le carter (ou enveloppe) de cette chambre sont réalisés dans un même matériau, généralement de type métallique. Cependant, dans certaines conditions particulières d'utilisation mettant en oeuvre des températures de combustion notablement élevées, l'emploi d'une chambre métallique s'avère d'un point de vue thermique totalement inadaptée et il doit être recouru à une chambre à base de matériaux composites haute température de type CMC. Toutefois, les difficultés de mise en oeuvre et le coût de ces matériaux font que leur utilisation est le plus souvent limitée à la chambre de combustion elle même, le distributeur d'entrée de la turbine haute pression et le carter restant alors réalisés plus classiquement en des matériaux métalliques. Or, les matériaux métalliques et les matériaux composites ont des coefficients de dilatation thermique très différents. Il en résulte des problèmes particulièrement aigus de liaison avec entre le carter et la chambre de combustion et d'étanchéité au niveau du distributeur, en entrée de la turbine haute pression. Le brevet US 6 131 384 montre une turbomachine selon cet art antérieur.Conventionally, in a turbojet or a turboprop, the high pressure turbine, including its inlet nozzle (HPT nozzle), the combustion chamber and the casing (or envelope) of this chamber are made of the same material, generally of the type metallic. However, under certain particular conditions of use involving significantly high combustion temperatures, the use of a metal chamber is from a thermal point of view totally inadequate and it must be resorted to a chamber based on CMC type high temperature composite materials. However, the difficulties of implementation and the cost of these materials mean that their use is most often limited to the combustion chamber itself, the inlet valve of the high pressure turbine and the casing then remaining more conventionally achieved. metallic materials. However, metal materials and composite materials have very different coefficients of thermal expansion. This results in particularly acute problems of connection with the housing and the combustion chamber and sealing at the distributor at the inlet of the high pressure turbine. The US Patent 6,131,384 shows a turbomachine according to this prior art.

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

La présente invention pallie ces inconvénients en proposant un montage de la chambre de combustion dans le carter ayant la capacité d'absorber les déplacements induits par les différences des coefficients de dilatation de ces pièces.The present invention overcomes these disadvantages by proposing a mounting of the combustion chamber in the casing having the capacity to absorb the displacements induced by the differences in the expansion coefficients of these parts.

Ce but est atteint par une turbomachine comportant, dans une enveloppe en matériau métallique et selon un sens F d'écoulement des gaz, un système d'injection d'un carburant, une chambre de combustion en matériau composite ayant un axe longitudinal, et un distributeur en matériau métallique formant l'étage d'entrée à aubes fixes d'une turbine haute pression, caractérisée en ce que ladite chambre de combustion en matériau composite est maintenue en position dans ladite enveloppe métallique par une pluralité de pattes métalliques souples ayant des premières et des secondes extrémités, lesdites premières extrémités étant reliées entre elles par une couronne métallique formant bride fixée à ladite enveloppe métallique par des premiers moyens de fixation et lesdites secondes extrémités étant fixées chacune conjointement par des seconds moyens de fixation d'une part à ladite chambre de combustion en matériau composite et d'autre part à une extrémité d'une paroi en matériau composite dont l'autre extrémité forme un plan d'appui pour un élément d'étanchéité solidaire dudit distributeur et assurant l'étanchéité de la veine de gaz entre ladite chambre de combustion et ledit distributeur, la souplesse desdites pattes de fixation permettant à des températures élevées une libre dilatation radiale de ladite chambre de combustion en matériau composite par rapport à ladite enveloppe métallique.This object is achieved by a turbomachine comprising, in an envelope of metallic material and in a direction F of gas flow, a fuel injection system, a composite material combustion chamber having a longitudinal axis, and a metal material distributor forming the fixed blade inlet stage of a high pressure turbine, characterized in that said composite material combustion chamber is held in position in said metal casing by a plurality of flexible metal tabs having first and second ends, said first ends being interconnected by a metal flange crown fixed to said metal shell by first fixing means and said second ends being each fixed jointly by second fixing means on the one hand to said chamber of composite material combustion and secondly at one end of a composite material wall whose other end forms a support plane for a sealing element integral with said distributor and ensuring the sealing of the gas stream between said combustion chamber and said distributor, the flexibility of said fixing lugs permitting at high temperatures radial free expansion of said combustion chamber made of composite material with respect to said metal casing.

Avec cette structure particulière de liaison fixe, les différentes usures dues aux corrosions de contact des systèmes de l'art antérieur peuvent être évitées. L'utilisation d'une paroi en matériau composite disposée dans le prolongement de la chambre de combustion pour réaliser l'étanchéité de la veine permet de plus de reconstituer la structure initiale de la chambre. En outre, la présence des pattes métalliques souples en lieu et place des brides traditionnelles permet un gain en masse particulièrement appréciable. Ces pattes, de part leur souplesse, permettent de supporter facilement l'écart de dilatation apparaissant aux températures élevées entre pièces métalliques et composites (en reprenant les déplacements dus à la dilatation) tout en assurant un parfait maintien et un bon centrage de la chambre de combustion dans l'enveloppe.With this particular structure of fixed connection, the different wear due to contact corrosion of systems of the prior art can be avoided. The use of a wall of composite material disposed in the extension of the combustion chamber to achieve the sealing of the vein also allows to reconstitute the initial structure of the chamber. In addition, the presence of flexible metal tabs instead of traditional flanges allows a particularly significant gain in mass. These tabs, because of their flexibility, allow to easily withstand the expansion gap occurring at high temperatures between metal parts and composites (taking the displacements due to expansion) while ensuring a perfect fit and a good centering of the chamber. combustion in the envelope.

Les premiers et seconds moyens de fixation sont constitués de préférence par une pluralité de boulons. Toutefois, les seconds moyens de fixation peuvent aussi être constitués par des éléments de sertissage. Avantageusement, ledit élément d'étanchéité est du type joint circulaire « à lamelles ». Il peut comporter une pluralité d'orifices de fuite calibrés.The first and second fastening means are preferably constituted by a plurality of bolts. However, the second fixing means can also be constituted by crimping elements. Advantageously, said sealing element is of the type "circular seal". It may comprise a plurality of calibrated leakage orifices.

Selon un mode de réalisation avantageux dans lequel l'enveloppe métallique est formée en deux parties, ladite couronne métallique reliant entre elles lesdites premières extrémités desdites pattes métalliques souples est montée entre des brides de liaison de ces deux parties. Dans un mode de réalisation alternatif, ladite couronne métallique peut être fixée directement à ladite enveloppe annulaire par des moyens de fixation conventionnels.According to an advantageous embodiment in which the metal casing is formed in two parts, said metal ring interconnecting said first ends of said flexible metal tabs is mounted between connecting flanges of these two parts. In an alternative embodiment, said metal ring may be fixed directly to said annular casing by conventional fastening means.

Selon le mode de réalisation envisagé, lesdites premières extrémités des pattes de fixation peuvent soit être fixées par brasage (ou soudage) à ladite couronne métallique formant bride soit former une pièce unique avec cette couronne métallique.According to the embodiment envisaged, said first ends of the fixing lugs may either be fixed by brazing (or welding) to said metal flange ring or form a single piece with this metal ring.

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 zone centrale d'une turbomachine dans un premier mode de réalisation de l'invention,
  • les figures 1A et 1B illustrent respectivement en perspective et en coupe des éléments de détail de la figure 1,
  • la figure 2 est une vue agrandie d'une partie de la figure 1 dans une première configuration de liaison alternative, et
  • la figure 3 est une vue agrandie d'une autre partie de la figure 1 dans une seconde configuration de liaison alternative.
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:
  • Figure 1 is a schematic axial half-sectional view of a central zone of a turbomachine in a first embodiment of the invention,
  • Figures 1A and 1B respectively illustrate in perspective and in section details of Figure 1 ,
  • Figure 2 is an enlarged view of a part of Figure 1 in a first alternative link configuration, and
  • Figure 3 is an enlarged view of another part of Figure 1 in a second alternative link configuration.

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 dans un premier mode de réalisation :

  • . une enveloppe annulaire externe (ou carter externe) en deux parties 12a, 12b en matériau métallique, d'axe longitudinal 10,
  • . une enveloppe annulaire interne (ou carter interne) coaxiale en deux parties 14a, 14b également en matériau métallique,
  • . un espace annulaire 16 compris entre les deux enveloppes 12a, 12b et 14a, 14b 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 (dont on peut noter la grille diffuseur 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 une partie amont 12a de l'enveloppe annulaire externe (dans un souci de simplification des dessins le mélangeur et le déflecteur associés à chaque buse d'injection n'ont pas été représentés), ensuite une chambre de combustion 24 en matériau composite haute température, par exemple 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 par des boulons métalliques ou réfractaires à vis à tête conique, sur des extrémités amont 36, 38 de ces parois axiales 26, 28, ce fond de chambre 30 étant pourvu d'orifices 40 pour notamment permettre l'injection du carburant et d'une partie du comburant dans la chambre de combustion 24, et enfin un distributeur annulaire 42 en matériau métallique formant un étage d'entrée d'une turbine haute pression (non représentée) et comportant classiquement une pluralité d'aubes fixes 44 montées entre une plate-forme circulaire externe 46 et une plate-forme circulaire interne 48.
Figure 1 axial half-section shows a central portion of a turbojet engine or a turboprop engine (called a turbomachine in the following description) comprising in a first embodiment:
  • . an outer annular casing (or outer casing) in two parts 12a, 12b made of metallic material, of longitudinal axis 10,
  • . an inner annular casing (or inner casing) coaxial in two parts 14a, 14b also made of metallic material,
  • . an annular space 16 between the two envelopes 12a, 12b and 14a, 14b receiving the compressed oxidant, generally air, coming upstream of a compressor (not shown) of the turbomachine, through an annular duct of diffusion 18 (which may be noted the diffuser grid 18a) defining a general flow F of gas flow,
    this space 16 comprising, in the gas flow direction, firstly an injection assembly formed of a plurality of injection systems 20 regularly distributed around the conduit 18 and each having a fuel injection nozzle 22 fixed on an upstream portion 12a of the outer annular envelope (for the sake of simplification of the drawings the mixer and the deflector associated with each injection nozzle have not been shown), then a combustion chamber 24 of composite material high temperature, for example CMC or other type (carbon for 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 comprises flaps 32, 34 fixed by any suitable means, for example by metal bolts or refractory screws with conical head, on upstream ends 36, 38 of these axial walls 26 , 28, this chamber bottom 30 being provided with orifices 40 in particular to allow the injection of the fuel and a part of the oxidant into the combustion chamber 24, and finally an annular distributor 42 of metallic material forming a stage of inlet of a high pressure turbine (not shown) and conventionally comprising a plurality of stationary vanes 44 mounted between an outer circular platform 46 and an inner circular platform 48.

Le distributeur est fixé sur une partie aval 14b de l'enveloppe annulaire interne de la turbomachine par des premiers moyens de fixation amovibles constitués de préférence par une pluralité de boulons 50 tout en reposant sur des moyens support 49 solidaire de l'enveloppe annulaire externe de la turbomachine.The distributor is fixed on a downstream portion 14b of the inner annular envelope of the turbomachine by first removable fastening means preferably constituted by a plurality of bolts 50 while resting on support means 49 integral with the outer annular envelope of the turbomachine.

Des orifices de passage 54, 56 ménagés dans les plates-formes métalliques externe 46 et interne 48 du distributeur 42 sont en outre prévus pour assurer un refroidissement des aubes fixes 44 de ce distributeur en entrée du rotor de la turbine haute pression à partir du comburant comprimé disponible en sortie du conduit de diffusion 18 et s'écoulant en deux flux F1, F2 de part et d'autre de la chambre de combustion 24.Through-holes 54, 56 formed in the outer metal 46 and inner 48 metal platforms of the distributor 42 are furthermore provided for cooling the vanes 44 of the distributor at the inlet of the rotor of the high-pressure turbine from the oxidant compressed available at the outlet of the diffusion duct 18 and flowing in two flows F1, F2 on either side of the combustion chamber 24.

Selon l'invention, la chambre de combustion 24, qui a un coefficient de dilatation thermique très différent des autres pièces métalliques formant la turbomachine, est maintenue fixement en position dans son enveloppe par une pluralité de pattes souples 58, 60 régulièrement réparties autour de la chambre de combustion entre les enveloppes annulaires interne et externe. Ces pattes de fixation sont montées pour une première partie d'entre elles (voir la patte référencée 58) entre l'enveloppe annulaire externe 12a, 12b et la paroi axiale externe 26 de la chambre de combustion et pour une seconde partie (comme la patte 60) entre l'enveloppe annulaire interne 14a, 14b et la paroi axiale interne 28 de la chambre de combustion. Le nombre de pattes peut, par exemple, être en nombre égal à celui des buses d'injection ou égal à un multiple de ce nombre.According to the invention, the combustion chamber 24, which has a coefficient of thermal expansion very different from the other metal parts forming the turbomachine, is fixedly held in position in its envelope by a plurality of flexible tabs 58, 60 regularly distributed around the combustion chamber between the inner and outer annular envelopes. These attachment tabs are mounted for a first part of them (see the tab referenced 58) between the outer annular casing 12a, 12b and the outer axial wall 26 of the combustion chamber and for a second part (such as the tab 60) between the inner annular envelope 14a, 14b and the inner axial wall 28 of the combustion chamber. The number of legs may, for example, be in number equal to that of the injection nozzles or equal to a multiple of this number.

Chaque patte de fixation souple en matériau métallique qui peut présenter une forme sensiblement triangulaire comme l'illustre la figure 1A, ou être constituée d'une simple lame (non représentée de largeur constante ou non), est soudée ou brasée par une première extrémité 62 ; 64 à une couronne métallique 66a, 66b formant bride et fixée solidairement par des premiers moyens de fixation 52 ; 68 à l'une ou l'autre (selon son emplacement) des enveloppes annulaires métalliques externe ou interne. Cette fixation par bride est destinée à faciliter le maintien de ces pattes sur les enveloppes métalliques. Dans un mode de réalisation préférentiel, ces pattes et la couronne métallique forment ensemble une pièce métallique unique d'un seul tenant.Each flexible fastening clip of metal material which can have a substantially triangular shape as illustrated Figure 1A , or consist of a single blade (not shown constant width or not), is welded or soldered by a first end 62; 64 to a metal ring 66a, 66b forming a flange and secured integrally by first fixing means 52; 68 to one or the other (depending on its location) of the outer or inner metal annular envelopes. This attachment flange is intended to facilitate the maintenance of these legs on the metal shells. In a preferred embodiment, these tabs and the metal ring together form a single piece of metal in one piece.

A une seconde extrémité 70 ;72, cette patte est fixée conjointement par des seconds moyens de fixation 74, 76 d'une part à une extrémité aval 88 ; 90 des parois axiales externe 26 et interne 28 de la chambre de combustion en matériau composite céramique et d'autre part à une extrémité d'une paroi en composite céramique 78a ; 78b disposée dans le prolongement de chacune des parois axiales externe et interne, formant en quelque sorte une seconde partie de chambre, et dont l'autre extrémité forme un plan d'appui pour un élément d'étanchéité solidaire du distributeur et assurant l'étanchéité de la veine de gaz entre la chambre de combustion 24 et le distributeur 42.At a second end 70, 72, this tab is fixed jointly by second fixing means 74, 76 on the one hand at a downstream end 88; 90 of the external axial walls 26 and inner 28 of the combustion chamber made of ceramic composite material and secondly at one end of a ceramic composite wall 78a; 78b disposed in the extension of each of the outer and inner axial walls, forming a kind of a second chamber portion, and the other end forms a support plane for a sealing element integral with the distributor and sealing the gas stream between the combustion chamber 24 and the distributor 42.

Dans le mode de réalisation de l'invention illustré à la figure 1, la liaison des secondes extrémités des pattes 70, 72 avec les extrémités aval des parois de la chambre de combustion et les premières extrémités des parois en composite céramique formant seconde partie de chambre est effectuée par un simple boulonnage, de préférence de type à écrou prisonnier pour faciliter un éventuel montage/démontage et corrélativement limiter le dimensionnement des pattes. La couronne métallique 66a, 66b reliant entre elles les premières extrémités 62, 64 des pattes est quant à elle de préférence prise entre des brides de liaison existantes entre les parties amont 12a, 14a et aval 12b, 14b des enveloppes annulaires interne et externe et maintenues fixement par les premiers moyens de fixation 52, 68 qui de préférence sont aussi de type boulon. On notera la présence de rondelles en matériau composite céramique 74a ; 76a pour permettre de « noyer» les têtes coniques des vis des boulons formant les seconds moyens de fixation 74 ; 76.In the embodiment of the invention illustrated in Figure 1 , the connection of the second ends of the tabs 70, 72 with the downstream ends of the walls of the combustion chamber and the first ends of the ceramic composite walls forming the second chamber portion is carried out by a simple bolting, preferably of prison nut type to facilitate a possible assembly / disassembly and correlatively limit the dimensions of the legs. The metal ring 66a, 66b interconnecting the first ends 62, 64 of the tabs is in turn preferably taken between existing connecting flanges between the upstream portions 12a, 14a and downstream 12b, 14b of the inner and outer annular envelopes and maintained fixedly by the first attachment means 52, 68 which are preferably also bolt type. Note the presence of washers ceramic composite material 74a; 76a to allow to "drown" the conical heads of the screws of the bolts forming the second attachment means 74; 76.

L'étanchéité de la veine de gaz entre la chambre de combustion 24 et le distributeur 42 est assurée par un joint circulaire « à lamelles » 80, 82 monté dans une rainure 84, 86 de chacune des plates-formes externe 46 et interne 48 du distributeur et qui vient s'appuyer directement sur la seconde partie d'extrémité de la paroi composite céramique 78a ; 78b formant un plan d'appui pour ce joint circulaire d'étanchéité. Le joint est maintenu en appui contre cette seconde extrémité de la paroi en composite au moyen d'un élément élastique, de type ressort à lames 92, 94, fixé sur le distributeur. Par cette disposition, il est assuré une parfaite continuité de la veine chaude entre la chambre de combustion 24 et le distributeur 42. Toutefois, pour assurer le refroidissement de la zone morte créée sous le distributeur 46 par la paroi en composite, des orifices de fuite calibrés 110 (illustrés sur la seule figure 1B) sont avantageusement prévus au niveau des joints 80, 82.The tightness of the gas stream between the combustion chamber 24 and the distributor 42 is provided by a "flap" circular seal 80, 82 mounted in a groove 84, 86 of each of the outer 46 and inner 48 platforms. dispenser and which bears directly on the second end portion of the ceramic composite wall 78a; 78b forming a support plane for this seal circular sealing. The seal is held in abutment against this second end of the composite wall by means of a resilient element, leaf spring type 92, 94, fixed on the distributor. By this arrangement, it is ensured a perfect continuity of the hot vein between the combustion chamber 24 and the distributor 42. However, to ensure the cooling of the dead zone created under the distributor 46 by the composite wall, leak holes calibrated 110 (illustrated on the only Figure 1B ) are advantageously provided at the joints 80, 82.

Quant à l'étanchéité des flux d'écoulement de gaz entre la chambre de combustion et la turbine, il est réalisé d'une part par un joint circulaire d'étanchéité de type « oméga » 96 monté dans une rainure circulaire 98 d'une bride de l'enveloppe annulaire interne 14 en contact direct avec la plate-forme circulaire interne 48 du distributeur et d'autre part par un autre joint circulaire « à lamelles » 100 monté dans une gorge circulaire 102 de la plate-forme circulaire externe du distributeur 46 et dont une extrémité est en contact direct avec un béquet circulaire 104 de la partie aval 12b de l'enveloppe annulaire externe.As regards the sealing of the gas flow flows between the combustion chamber and the turbine, it is formed firstly by an omega-type circular seal 96 mounted in a circular groove 98 of a flange of the inner annular casing 14 in direct contact with the inner circular platform 48 of the distributor and secondly by another "flap" circular seal 100 mounted in a circular groove 102 of the outer circular platform of the distributor 46 and one end is in direct contact with a circular spoiler 104 of the downstream portion 12b of the outer annular envelope.

La figure 1B illustre une première variante du mode de réalisation précédent dans lequel la fixation des pattes (seul le cas de la patte 60 est illustré) à l'extrémité aval 90 de la chambre de combustion 24 est effectuée par une liaison sertie, les boulons 76 étant remplacés par des éléments de sertissage 76b. Avec cette configuration, le refroidissement pouvant s'effectuer au travers des éléments de sertissage, il n'est plus nécessaire de prévoir des orifices calibrés au niveau des joint à lamelles 80, 82. Figure 1B illustrates a first variant of the previous embodiment in which the attachment of the tabs (only the case of the tab 60 is illustrated) at the downstream end 90 of the combustion chamber 24 is performed by a crimped connection, the bolts 76 being replaced by crimping elements 76b. With this configuration, the cooling being able to take place through the crimping elements, it is no longer necessary to provide calibrated orifices at the lamellae joints 80, 82.

Dans une variante illustrée à la figure 2, la couronne métallique 66a formant bride reliant entre elles par brasage (ou soudage) les premières extrémités 62 des pattes de fixation 58 de la paroi axiale externe de la chambre de combustion 26 n'est plus montée entre brides mais elle même brasée (ou soudée) au niveau d'un détrompeur 106 centré et en appui sur l'enveloppe annulaire externe 12.In a variant illustrated in Figure 2 , the metal ring 66a forming a flange interconnecting by brazing (or welding) the first ends 62 of the fastening tabs 58 of the outer axial wall of the combustion chamber 26 is no longer mounted between flanges but itself brazed (or welded) ) at a polarizer 106 centered and resting on the outer annular casing 12.

Dans une autre variante illustrée à la figure 3, la couronne métallique 66b formant bride reliant entre elles par brasage (ou soudage) les premières extrémités 64 des pattes de fixation 60 de la paroi axiale interne de la chambre de combustion 28 n'est plus montée entre brides mais simplement fixée directement à l'enveloppe annulaire interne 14 par des moyens de fixation conventionnels 108, par exemple de type boulon.In another variant illustrated in Figure 3 , the metal ring 66b forming a flange interconnecting by brazing (or welding) the first ends 64 of the fixing lugs 60 of the inner axial wall of the combustion chamber 28 is no longer mounted between flanges but simply fixed directly to the inner annular casing 14 by conventional fastening means 108, for example of the bolt type.

Dans toutes les configurations précitées, la souplesse des pattes de fixation permet de supporter l'écart de dilatation thermique apparaissant aux températures élevées entre la chambre de combustion en matériau composite et les enveloppes annulaires métalliques tout en assurant le maintien et le positionnement de la chambre.In all the aforementioned configurations, the flexibility of the fixing lugs makes it possible to withstand the thermal expansion gap occurring at the temperatures elevated between the composite material combustion chamber and the metal annular envelopes while ensuring the maintenance and positioning of the chamber.

Claims (9)

  1. A turbomachine comprising a shell of metal material (12a, 12b; 14a, 14b) containing in a gas flow direction F: a fuel injector assembly (20, 22), a composite material combustion chamber (24) having a longitudinal axis (10), and a metal nozzle (42) forming the fixed blade inlet stage (44) of a high pressure turbine, characterised in that said composite material combustion chamber is held in position inside said metal shell by a plurality of flexible metal tabs (58, 60) having first and second ends (62, 64; 70, 72), said first ends being interconnected by a flange-forming metal ring (66a, 66b) fixed to said metal shell by first fixing means (52; 68, 108), and each of said second ends being fixed by second fixing means (74, 76) both to said composite material combustion chamber (26, 28) and to one end of a composite material wall (78a, 78b) whose other end forms a bearing plane for a sealing element (80, 82) secured to said nozzle and providing sealing for the stream of gas between said combustion chamber and said nozzle, the flexibility of said metal fixing tabs allowing expansion to take place freely in a radial direction at high temperatures between said composite material combustion chamber and said metal shell.
  2. A turbomachine according to claim 1, characterised in that said first and second fixing means are constituted by a plurality of bolts.
  3. A turbomachine according to claim 1, characterised in that said metal shell is made up of two portions (12a, 12b; 14a, 14b), and said metal ring interconnecting said first ends of said flexible metal tabs is mounted between the connection flanges of said two portions.
  4. A turbomachine according to claim 1, characterised in that said metal ring interconnecting said first ends of said flexible metal tabs is fixed directly to said annular shell by conventional fixing means (108).
  5. A turbomachine according to claim 1, characterised in that said first ends of the flexible metal tabs are fixed by brazing (or welding) to said flange-formning metal ring.
  6. A turbomachine according to claim 1, characterised in that said first ends of the flexible metal tabs are integrally formed with said flange-forming metal ring.
  7. A turbomachine according to claim 1, characterised in that said second fixing means are constituted by crimping elements (76b).
  8. A turbomachine according to claim 1, characterised in that said sealing element is of the circular spring blade gasket type (80, 82).
  9. A turbomachine according to claim 8, characterised in that said spring blade gasket includes a plurality of calibrated leakage orifices (110).
EP02291364A 2001-06-06 2002-06-04 Double mounting of a ceramic matrix composite combustion chamber Expired - Lifetime EP1265035B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0107372 2001-06-06
FR0107372A FR2825785B1 (en) 2001-06-06 2001-06-06 TWO-PIECE TURBOMACHINE CMC COMBUSTION CHAMBER LINKAGE

Publications (2)

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EP1265035A1 EP1265035A1 (en) 2002-12-11
EP1265035B1 true EP1265035B1 (en) 2008-02-13

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US (1) US6675585B2 (en)
EP (1) EP1265035B1 (en)
JP (1) JP4097994B2 (en)
DE (1) DE60224956T2 (en)
FR (1) FR2825785B1 (en)

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DE60224956D1 (en) 2008-03-27
DE60224956T2 (en) 2009-02-05
FR2825785A1 (en) 2002-12-13
FR2825785B1 (en) 2004-08-27
US6675585B2 (en) 2004-01-13
US20020184888A1 (en) 2002-12-12
JP2003035418A (en) 2003-02-07
EP1265035A1 (en) 2002-12-11
JP4097994B2 (en) 2008-06-11

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