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EP1265035A1 - 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
EP1265035A1
EP1265035A1 EP02291364A EP02291364A EP1265035A1 EP 1265035 A1 EP1265035 A1 EP 1265035A1 EP 02291364 A EP02291364 A EP 02291364A EP 02291364 A EP02291364 A EP 02291364A EP 1265035 A1 EP1265035 A1 EP 1265035A1
Authority
EP
European Patent Office
Prior art keywords
metal
combustion chamber
turbomachine according
fixing means
distributor
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP02291364A
Other languages
German (de)
French (fr)
Other versions
EP1265035B1 (en
Inventor
Didier Hernandez
Gwenaelle Calvez
Alexandre Forestier
Eric Conete
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA Moteurs SA
SNECMA SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by SNECMA Moteurs SA, SNECMA SAS filed Critical SNECMA Moteurs SA
Publication of EP1265035A1 publication Critical patent/EP1265035A1/en
Application granted granted Critical
Publication of EP1265035B1 publication Critical patent/EP1265035B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—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 turbomachinery and it is more particularly interested in the problem posed by the assembly of a CMC type composite material combustion chamber (ceramic matrix composite) in the metal casing of a turbomachine.
  • the turbine high pressure in particular its inlet distributor (HPT nozzle), the combustion as well as the casing (or casing) of this chamber are produced in the same material, generally of metallic type.
  • HPT nozzle inlet distributor
  • the combustion as well as the casing (or casing) of this chamber are produced in the same material, generally of metallic type.
  • the use of a metal chamber proves to be totally unsuitable thermal point of view and it must be resorted to a room based on CMC type high temperature composite materials.
  • difficulties of implementation and the cost of these materials make their use is most often limited to the combustion chamber itself, the distributor inlet of the high pressure turbine and the remaining casing then produced more conventionally made of metallic materials.
  • metallic materials and composite materials have very different coefficients of thermal expansion. This results in particularly acute problems of connection with between the casing and the combustion and sealing chamber at the distributor, at the inlet of the high pressure turbine.
  • the present invention overcomes these drawbacks by proposing an assembly of the combustion chamber in the crankcase having the capacity to absorb the displacements induced by the differences in the expansion coefficients of these rooms.
  • a turbomachine comprising, in an envelope made of metallic material and in a direction F of gas flow, a system fuel injection, a combustion chamber made of composite material having a longitudinal axis, and a distributor of metallic material forming the input stage with fixed blades of a high pressure turbine, characterized in that said combustion chamber of composite material is held in position in said metallic envelope by a plurality of flexible metallic tabs having first and second ends, said first ends being interconnected by a metal crown forming a flange fixed to said metal casing by first fixing means and said seconds ends each fixed together by second fixing means on the one hand to said combustion chamber of composite material and on the other hand to one end of a wall of composite material, the other end of which forms a support surface 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 allowing temperatures a free radial expansion of said combustion chamber made of material composite with respect to said metallic envelope.
  • the first and second fixing means preferably consist by a plurality of bolts.
  • the second fixing means can also be constituted by crimping elements.
  • said sealing element is of the “lamellar” circular joint type. It can include a plurality of calibrated leak holes.
  • the envelope metal is formed in two parts, said metal ring connecting between them said first ends of said flexible metal tabs is mounted between connecting flanges of these two parts.
  • said metal crown can be fixed directly to said annular casing by conventional fixing means.
  • said first ends of the fixing lugs can either be fixed by soldering (or welding) to said metal crown forming flange either form a single piece with this metal crown.
  • the distributor is fixed on a downstream part 14b of the annular casing internal of the turbomachine by first removable fixing means preferably consisting of a plurality of bolts 50 while resting on support means 49 secured to the outer annular envelope of the turbomachine.
  • Passage orifices 54, 56 formed in the metal platforms external 46 and internal 48 of the distributor 42 are further provided to ensure cooling of the stationary vanes 44 of this distributor at the inlet of the rotor of the high pressure turbine from the compressed oxidizer available at the outlet of the diffusion duct 18 and flowing in two streams F1, F2 on either side of the combustion chamber 24.
  • the combustion chamber 24 which has a coefficient of thermal expansion very different from 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 chamber combustion between the inner and outer annular shells.
  • These legs fasteners are fitted for a first part of them (see tab referenced 58) between the outer annular envelope 12a, 12b and the axial wall external 26 of the combustion chamber and for a second part (like the tab 60) between the internal annular envelope 14a, 14b and the internal axial wall 28 of the combustion chamber.
  • the number of legs can, for example, be number equal to that of the injection nozzles or equal to a multiple of this number.
  • Each flexible fixing lug made of metallic material which may have a substantially triangular shape as illustrated in FIG. 1A, or to be consisting of a simple blade (not shown of constant width or not), is welded or brazed by a first end 62; 64 to a metal crown 66a, 66b forming a flange and fixed integrally by first fixing means 52; 68 to one or the other (depending on its location) of the annular envelopes metallic external or internal.
  • This flange fixing is intended to facilitate the retention of these legs on the metal envelopes.
  • these legs and the metal crown together form a unique metal piece 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 external axial 26 and internal 28 walls of the material combustion chamber ceramic composite and on the other hand at one end of a composite wall ceramic 78a; 78b arranged in the extension of each of the axial walls external and internal, sort of forming a second part of the chamber, and the other end of which forms a support plane for a sealing element integral with the distributor and ensuring the tightness of the gas stream between the combustion chamber 24 and the distributor 42.
  • connection second ends of the legs 70, 72 with the downstream ends of the walls of the combustion chamber and the first ends of the composite walls ceramic forming the second part of the chamber is carried out by a simple bolting, preferably of captive nut type to facilitate possible assembly / disassembly and correspondingly limit the sizing of the legs.
  • the metal crown 66a, 66b connecting the first ends 62, 64 legs is preferably taken between existing connecting flanges between the upstream parts 12a, 14a and downstream 12b, 14b of the internal annular envelopes and external and fixedly held by the first fixing means 52, 68 which preferably are also of the bolt type.
  • the tightness of the gas stream between the combustion chamber 24 and the distributor 42 is provided by a “lamellar” circular joint 80, 82 mounted in a groove 84, 86 of each of the external 46 and internal 48 platforms of the distributor and which comes to rest directly on the second end part of the ceramic composite wall 78a; 78b forming a support plane for this joint sealing circular.
  • the seal is held in abutment against this second end of the composite wall by means of an elastic element, of the type leaf spring 92, 94, fixed on the distributor.
  • FIG. 1B illustrates a first variant of the embodiment previous in which the fixing of the legs (only the case of the leg 60 is illustrated) to the downstream end 90 of the combustion chamber 24 is effected by a connection crimped, the bolts 76 being replaced by crimping elements 76b.
  • the cooling being able to be carried out through elements crimping, it is no longer necessary to provide calibrated orifices at the lamellar seal 80, 82.
  • the metal crown 66a forming a flange connecting together the first ends by brazing (or welding) 62 of the fixing lugs 58 of the external axial wall of the combustion 26 is no longer mounted between flanges but itself brazed (or welded) at a centered key 106 and resting on the annular casing external 12.
  • the metal crown 66b forming a flange connecting together the first ends by brazing (or welding) 64 of the fixing lugs 60 of the internal axial wall of the combustion chamber 28 is no longer mounted between flanges but simply fixed directly to the internal annular envelope 14 by conventional fixing means 108, for example of the bolt type.
  • the flexibility of the fixing lugs supports the thermal expansion gap occurring at temperatures between the composite material combustion chamber and the casings metallic annulars while ensuring the maintenance and positioning of the bedroom.

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

Abstract

The gas turbine engine combustor has an annular combustion chamber of composite material held in position between the metal annular envelope rings by metal flanges (58,60). The flanges are attached at one end to a metal collar (65,66) forming a fixed flange on each envelope ring by fixings (52,66). The other end of the flanges are attached to the composite combustion chamber and to a chamber wall.

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 turbomachinery and it is more particularly interested in the problem posed by the assembly of a CMC type composite material combustion chamber (ceramic matrix composite) 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.Conventionally, in a turbojet or a turboprop, the turbine high pressure, in particular its inlet distributor (HPT nozzle), the combustion as well as the casing (or casing) of this chamber are produced in the same material, generally of metallic type. However, in some special conditions of use using temperatures of significantly higher combustion, the use of a metal chamber proves to be totally unsuitable thermal point of view and it must be resorted to a room based on CMC type high temperature composite materials. However, difficulties of implementation and the cost of these materials make their use is most often limited to the combustion chamber itself, the distributor inlet of the high pressure turbine and the remaining casing then produced more conventionally made of metallic materials. However, metallic materials and composite materials have very different coefficients of thermal expansion. This results in particularly acute problems of connection with between the casing and the combustion and sealing chamber at the distributor, at the inlet of the high pressure turbine.

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 drawbacks by proposing an assembly of the combustion chamber in the crankcase having the capacity to absorb the displacements induced by the differences in the expansion coefficients of these rooms.

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 made of metallic material and in a direction F of gas flow, a system fuel injection, a combustion chamber made of composite material having a longitudinal axis, and a distributor of metallic material forming the input stage with fixed blades of a high pressure turbine, characterized in that said combustion chamber of composite material is held in position in said metallic envelope by a plurality of flexible metallic tabs having first and second ends, said first ends being interconnected by a metal crown forming a flange fixed to said metal casing by first fixing means and said seconds ends each fixed together by second fixing means on the one hand to said combustion chamber of composite material and on the other hand to one end of a wall of composite material, the other end of which forms a support surface 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 allowing temperatures a free radial expansion of said combustion chamber made of material composite with respect to said metallic envelope.

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 fixed connection structure, the various wear due contact corrosion of prior art systems can be avoided. The use of a wall of composite material arranged in the extension of the combustion chamber for sealing the vein allows more reconstruct the initial structure of the room. In addition, the presence of the legs flexible metal instead of traditional flanges allows a gain in particularly appreciable mass. These legs, due to their flexibility, allow easily withstand the expansion gap occurring at high temperatures between metallic and composite parts (taking up the displacements due to the dilation) while ensuring perfect support and 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 fixing means preferably consist by a plurality of bolts. However, the second fixing means can also be constituted by crimping elements. Advantageously, said sealing element is of the “lamellar” circular joint type. It can include a plurality of calibrated leak holes.

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 envelope metal is formed in two parts, said metal ring connecting between them said first ends of said flexible metal tabs is mounted between connecting flanges of these two parts. In one embodiment alternative, said metal crown can be fixed directly to said annular casing by conventional fixing 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 can either be fixed by soldering (or welding) to said metal crown forming flange either form a single piece with this metal crown.

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 characteristics and advantages of the present invention will emerge more clearly from the following description, given by way of non-limiting illustration, with reference to the appended drawings in which:
  • FIG. 1 is a schematic view in axial half-section of a central zone of a turbomachine in a first embodiment of the invention,
  • FIGS. 1A and 1B respectively illustrate in perspective and in section elements of detail in FIG. 1,
  • FIG. 2 is an enlarged view of part of FIG. 1 in a first alternative connection configuration, and
  • Figure 3 is an enlarged view of another part of Figure 1 in a second alternative connection 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.
FIG. 1 shows in axial half-section a central part of a turbojet engine or a turboprop engine (called a turbomachine in the following description) comprising in a first embodiment:
  • an outer annular casing (or outer casing) in two parts 12a, 12b made of metallic material, with a longitudinal axis 10,
  • an internal annular casing (or internal casing) coaxial in two parts 14a, 14b also made of metallic material,
  • an annular space 16 comprised between the two envelopes 12a, 12b and 14a, 14b receiving the compressed oxidizer, generally air, coming upstream from a compressor (not shown) of the turbomachine, through an annular duct of diffusion 18 (of which the diffuser grid 18a may be noted) 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 on an upstream part 12a of the outer annular casing (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 made of composite material high temperature, for example of the CMC or other type (carbon for example), formed by an external axial wall 26 and an internal axial wall 28, both coaxial with axis 10, and a transverse wall 30 which constitutes the bottom of this combustion chamber and which includes flaps 32, 34 fixed by any suitable means, for example by metal or refractory bolts with conical head screws, on upstream ends 36, 38 of these axial walls 26 , 28, this chamber bottom 30 being provided with orifices 40 for in particular allowing the injection of fuel and 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 fixed vanes 44 mounted between an external circular platform 46 and an internal 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 part 14b of the annular casing internal of the turbomachine by first removable fixing means preferably consisting of a plurality of bolts 50 while resting on support means 49 secured to 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.Passage orifices 54, 56 formed in the metal platforms external 46 and internal 48 of the distributor 42 are further provided to ensure cooling of the stationary vanes 44 of this distributor at the inlet of the rotor of the high pressure turbine from the compressed oxidizer available at the outlet of the diffusion duct 18 and flowing in two streams 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 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 chamber combustion between the inner and outer annular shells. These legs fasteners are fitted for a first part of them (see tab referenced 58) between the outer annular envelope 12a, 12b and the axial wall external 26 of the combustion chamber and for a second part (like the tab 60) between the internal annular envelope 14a, 14b and the internal axial wall 28 of the combustion chamber. The number of legs can, for example, be 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 fixing lug made of metallic material which may have a substantially triangular shape as illustrated in FIG. 1A, or to be consisting of a simple blade (not shown of constant width or not), is welded or brazed by a first end 62; 64 to a metal crown 66a, 66b forming a flange and fixed integrally by first fixing means 52; 68 to one or the other (depending on its location) of the annular envelopes metallic external or internal. This flange fixing is intended to facilitate the retention of these legs on the metal envelopes. In a mode of preferential embodiment, these legs and the metal crown together form a unique metal piece 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 external axial 26 and internal 28 walls of the material combustion chamber ceramic composite and on the other hand at one end of a composite wall ceramic 78a; 78b arranged in the extension of each of the axial walls external and internal, sort of forming a second part of the chamber, and the other end of which forms a support plane for a sealing element integral with the distributor and ensuring the tightness of 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 FIG. 1, the connection second ends of the legs 70, 72 with the downstream ends of the walls of the combustion chamber and the first ends of the composite walls ceramic forming the second part of the chamber is carried out by a simple bolting, preferably of captive nut type to facilitate possible assembly / disassembly and correspondingly limit the sizing of the legs. The metal crown 66a, 66b connecting the first ends 62, 64 legs is preferably taken between existing connecting flanges between the upstream parts 12a, 14a and downstream 12b, 14b of the internal annular envelopes and external and fixedly held by the first fixing means 52, 68 which preferably are also of the bolt type. Note the presence of washers in ceramic composite material 74a; 76a to allow the heads to be "drowned" tapered bolt screws forming the second fixing 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 “lamellar” circular joint 80, 82 mounted in a groove 84, 86 of each of the external 46 and internal 48 platforms of the distributor and which comes to rest directly on the second end part of the ceramic composite wall 78a; 78b forming a support plane for this joint sealing circular. The seal is held in abutment against this second end of the composite wall by means of an elastic element, of the type leaf spring 92, 94, fixed on the distributor. By this provision, he is assured perfect continuity of the hot stream between the combustion chamber 24 and the distributor 42. However, to cool the dead zone created under the distributor 46 through the composite wall, calibrated leak holes 110 (illustrated in FIG. 1B only) 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 for the tightness of the gas flow flows between the combustion and the turbine, it is produced on the one hand by a circular joint “Omega” type seal 96 mounted in a circular groove 98 of a flange of the internal annular casing 14 in direct contact with the platform internal circular 48 of the distributor and on the other hand by another circular joint “to slats "100 mounted in a circular groove 102 of the circular platform external of the distributor 46 and one end of which is in direct contact with a circular spoiler 104 of the downstream part 12b of the external 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.FIG. 1B illustrates a first variant of the embodiment previous in which the fixing of the legs (only the case of the leg 60 is illustrated) to the downstream end 90 of the combustion chamber 24 is effected by a connection crimped, the bolts 76 being replaced by crimping elements 76b. With this configuration, the cooling being able to be carried out through elements crimping, it is no longer necessary to provide calibrated orifices at the lamellar seal 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 FIG. 2, the metal crown 66a forming a flange connecting together the first ends by brazing (or welding) 62 of the fixing lugs 58 of the external axial wall of the combustion 26 is no longer mounted between flanges but itself brazed (or welded) at a centered key 106 and resting on the annular casing external 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 FIG. 3, the metal crown 66b forming a flange connecting together the first ends by brazing (or welding) 64 of the fixing lugs 60 of the internal axial wall of the combustion chamber 28 is no longer mounted between flanges but simply fixed directly to the internal annular envelope 14 by conventional fixing 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 above-mentioned configurations, the flexibility of the fixing lugs supports the thermal expansion gap occurring at temperatures between the composite material combustion chamber and the casings metallic annulars while ensuring the maintenance and positioning of the bedroom.

Claims (9)

Turbomachine comportant, dans une enveloppe en matériau métallique (12a, 12b ; 14a, 14b) et selon un sens F d'écoulement des gaz, un ensemble d'injection d'un carburant (20, 22), une chambre de combustion en matériau composite (24) ayant un axe longitudinal (10), et un distributeur en matériau métallique (42) formant l'étage d'entrée à aubes fixes (44) 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 (58, 60) ayant des premières (62, 64) et des secondes (70, 72) extrémités, lesdites premières extrémités étant reliées entre elles par une couronne métallique (66a, 66b) formant bride fixée à ladite enveloppe métallique par des premiers moyens de fixation (52 ; 68, 108) et lesdites secondes extrémités étant fixées chacune conjointement par des seconds moyens de fixation (74, 76) d'une part à ladite chambre de combustion en matériau composite (26, 28) et d'autre part à une extrémité d'une paroi en matériau composite (78a, 78b) dont l'autre extrémité forme un plan d'appui pour un élément d'étanchéité (80, 82) 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 métalliques permettant à des températures élevées une libre dilatation radiale de ladite chambre de combustion en matériau composite par rapport à ladite enveloppe métallique.Turbomachine comprising, in an envelope of metallic material (12a, 12b; 14a, 14b) and in a direction F of gas flow, a fuel injection assembly (20, 22), a combustion chamber made of material composite (24) having a longitudinal axis (10), and a distributor of metallic material (42) forming the input stage with fixed blades (44) of a high pressure turbine, characterized in that said combustion chamber in composite material is held in position in said metal casing by a plurality of flexible metal tabs (58, 60) having first (62, 64) and second (70, 72) ends, said first ends being connected to each other by a crown metal (66a, 66b) forming a flange fixed to said metal casing by first fixing means (52; 68, 108) and said second ends being each fixed jointly by second fixing means (74, 76) on the one hand to said combustion chamber of composite material (26, 28) and on the other hand at one end of a wall of composite material (78a, 78b), the other end of which forms a support plane for a sealing element (80 , 82) integral with said distributor and ensuring the tightness of the gas stream between said combustion chamber and said distributor, the flexibility of said metal fixing lugs allowing at high temperatures a free radial expansion of said combustion chamber of composite material by with respect to said metallic envelope. Turbomachine selon la revendication 1, caractérisée en ce que lesdits premiers et seconds moyens de fixation sont constitués par une pluralité de boulons.Turbomachine according to claim 1, characterized in that said first and second fixing means are constituted by a plurality of bolts. Turbomachine selon la revendication 1, caractérisée en ce que, ladite enveloppe métallique étant formée en deux parties (12a, 12b ; 14a, 14b), ladite couronne métallique reliant entre elles lesdites premières extrémités desdites pattes métalliques souples est montée entre des brides de liaison de ces deux parties. Turbomachine according to claim 1, characterized in that , said metal casing being formed in two parts (12a, 12b; 14a, 14b), said metal ring connecting together said first ends of said flexible metal tabs is mounted between connecting flanges these two parts. Turbomachine selon la revendication 1, caractérisée en ce que ladite couronne métallique reliant entre elles lesdites premières extrémités desdites pattes métalliques souples est fixée directement à ladite enveloppe annulaire par des moyens de fixation conventionnels (108).Turbomachine according to claim 1, characterized in that said metal ring connecting together said first ends of said flexible metal tabs is fixed directly to said annular casing by conventional fixing means (108). Turbomachine selon la revendication 1, caractérisée en ce que lesdites premières extrémités des pattes métalliques souples sont fixées par brasage (ou soudage) à ladite couronne métallique formant bride.Turbomachine according to claim 1, characterized in that said first ends of the flexible metal tabs are fixed by brazing (or welding) to said metal crown forming a flange. Turbomachine selon la revendication 1, caractérisée en ce que lesdites premières extrémités des pattes métalliques souples forment une pièce unique avec ladite couronne métallique formant bride.Turbomachine according to claim 1, characterized in that said first ends of the flexible metal legs form a single piece with said metal crown forming a flange. Turbomachine selon la revendication 1, caractérisée en ce que lesdits seconds moyens de fixation sont constitués par des éléments de sertissage (76b).Turbomachine according to claim 1, characterized in that said second fixing means are constituted by crimping elements (76b). Turbomachine selon la revendication 1, caractérisée en ce que ledit élément d'étanchéité est du type joint circulaire « à lamelles » (80, 82).Turbomachine according to Claim 1, characterized in that the said sealing element is of the "lamellar" circular joint type (80, 82). Turbomachine selon la revendication 8, caractérisée en ce que ledit joint « à lamelles » comporte une pluralité d'orifices de fuite calibrés (110).Turbomachine according to claim 8, characterized in that said "lamella" seal comprises a plurality of calibrated leak orifices (110).
EP02291364A 2001-06-06 2002-06-04 Double mounting of a ceramic matrix composite combustion chamber Expired - Lifetime EP1265035B1 (en)

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FR0107372A FR2825785B1 (en) 2001-06-06 2001-06-06 TWO-PIECE TURBOMACHINE CMC COMBUSTION CHAMBER LINKAGE
FR0107372 2001-06-06

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US6675585B2 (en) 2004-01-13
US20020184888A1 (en) 2002-12-12
FR2825785B1 (en) 2004-08-27
EP1265035B1 (en) 2008-02-13
DE60224956D1 (en) 2008-03-27
JP4097994B2 (en) 2008-06-11
JP2003035418A (en) 2003-02-07
FR2825785A1 (en) 2002-12-13
DE60224956T2 (en) 2009-02-05

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