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EP1265033B1 - Combustion chamber with a system for mounting the chamber end wall - Google Patents

Combustion chamber with a system for mounting the chamber end wall Download PDF

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Publication number
EP1265033B1
EP1265033B1 EP02291362A EP02291362A EP1265033B1 EP 1265033 B1 EP1265033 B1 EP 1265033B1 EP 02291362 A EP02291362 A EP 02291362A EP 02291362 A EP02291362 A EP 02291362A EP 1265033 B1 EP1265033 B1 EP 1265033B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
end wall
chamber according
side walls
fixed
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP02291362A
Other languages
German (de)
French (fr)
Other versions
EP1265033A1 (en
Inventor
Gwénaelle Calvez
Didier Hernandez
Alexandre Forestier
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 SAS
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Filing date
Publication date
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Publication of EP1265033A1 publication Critical patent/EP1265033A1/en
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Publication of EP1265033B1 publication Critical patent/EP1265033B1/en
Anticipated expiration legal-status Critical
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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
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2211/00—Thermal dilatation prevention or compensation

Definitions

  • the present invention relates to the specific field of turbomachines and is more particularly concerned with the problem posed by the mounting of a metal bottom of a combustion chamber of a turbomachine on the walls of composite material of the CMC type (ceramic matrix composite ) of this room.
  • a combustion chamber is known from US 5,291,732 .
  • the high pressure turbine in particular its inlet nozzle (HPT nozzle), the injection system, the combustion chamber and the annular envelope of this chamber are made of metal type.
  • HPT nozzle inlet nozzle
  • the injection system, the combustion chamber and the annular envelope of this chamber are made of metal type.
  • the use of an all-metal chamber is from a thermal point of view totally inadequate and it must be resorted to a chamber based on of high temperature composite materials of the CMC type.
  • the difficulties of implementation and the cost of these materials mean that their use is most often limited to the combustion chamber itself and more particularly to its only axial walls, the inlet valve of the high pressure turbine, the injection system and the annular envelope then remaining more typically made of metal materials.
  • metal materials and composite materials have very different coefficients of thermal expansion. This results in particularly acute problems especially at the level of the connection between the composite material walls of the combustion chamber and the metal chamber bottom.
  • the present invention overcomes these disadvantages by proposing a metal chamber bottom assembly having the capacity to absorb the displacements induced by the differences in the coefficients of expansion between this metal bottom and the composite walls of the combustion chamber.
  • annular combustion chamber comprising outer and inner axial walls of composite material and a chamber bottom of metallic material, characterized in that to allow radial free expansion of said chamber bottom with respect to said axial walls, said chamber bottom is held in position between said axial walls by a plurality of flexible tongues fixed on the one hand to said axial walls by fixing means and on the other hand to said bottom chamber by soldering or welding, said chamber bottom comprising besides means for sealing between said chamber bottom and said axial walls.
  • the flexible fastening tabs are made of a metallic material and the fastening means consist of a plurality of bolts, preferably with a prison nut.
  • the sealing means comprise a "slat" type circular seal mounted in a circular groove of said metal chamber bottom and intended to provide a bearing on said axial wall of the combustion chamber opposite.
  • the circular seal is sectored and is held in abutment against said axial wall by means of a resilient element fixed on said metal chamber bottom. This elastic element is constituted by a leaf spring.
  • the sealing means comprise a circular segment mounted against said axial wall and intended to cooperate with a circular groove of said metal chamber bottom.
  • this circular sealing segment is split.
  • the flexible tongues of attachment comprise a first end fixed to one or the other of said axial walls by said fixing means and a second end fixed by soldering or welding to said chamber bottom.
  • the chamber bottom may comprise in addition a metal ring on which are brazed or welded said second ends of said flexible fastening tongues.
  • the flexible fastening tabs comprise a first end attached to one of said axial walls by first connecting means a second end attached to the other of said axial walls by second connecting means and a part central fixed to the bottom of the chamber by soldering or welding.
  • these flexible fastening tabs are disposed between each of the injection nozzles.
  • the metal bottom 30 of the combustion chamber which has a coefficient of thermal expansion very different from that of the axial walls outer 26 and inner 28 of composite material of the combustion chamber, is fixedly held in position between these axial walls by a plurality of flexible tabs 36, 38 regularly distributed between the fuel injection nozzles 22 (see for example the figure 4 ).
  • These fixing tabs are mounted for a first series of them (see the tab referenced 36) between the metal bottom 30 and the outer axial wall 26 and for a second series of them (see the tab referenced 38) between the metal base 30 and the inner axial wall 28.
  • Each flexible fastening tongue is made of a metallic material and is preferably constituted by a thin blade, of constant width or not, having a point of attachment at each of its two ends. .
  • first end 42; 44 of the fastening tongue is fixed integrally and according to its location at one or the other of the outer axial walls 26 or inner 28 of the combustion chamber by first fixing means 46; 48 and the second end 50; 52 is preferably fixed by welding or brazing to a metal ring 54; 56, itself brazed or welded to the metal chamber bottom 30 of the combustion chamber.
  • This attachment absorbs the dilatations of the chamber bottom without damaging the composite axial walls that move little radially.
  • the first fastening means disposed offset from the injection nozzles are advantageously bolt type. And, to facilitate access and assembly / disassembly, these bolts are preferably chosen to type prison nut.
  • the seal between the outer or inner axial wall and the metal ring is provided by a "slat" type circular seal 58; 60 mounted in a circular groove 62; 64 of the metal crown.
  • This advantageously sectored seal comprises in its upstream part a spigot 66; 68 for providing an O-bearing on the facing axial wall 26; 28 of the combustion chamber.
  • the seal is pressed against the wall by an elastic member 70; 72, preferably a leaf spring, and held in position by a plurality of pins 74; 76 integral with the crown.
  • the clearance between the outer peripheral edge 78 of the chamber floor (and the edge corresponding of the metal ring) is calculated so that, in operation, the metal ring does not come to compress the outer axial wall 26 of composite material or simply does not come into contact with it.
  • the seal 60 sealing with the inner axial wall 28 is prestressed, the hot expansion of the chamber bottom having the effect of detaching the bottom of the inner wall.
  • the figure 2 illustrates a first variant embodiment of the attachment of the metal chamber bottom to the axial walls made of composite material of the combustion chamber, in which the chamber bottom and the metal crowns of the fixing tongues form a single piece 80 on which will be soldered or soldered directly the second ends of the tabs 50; 52.
  • This unique piece of course incorporates the previous sealing means.
  • a second variant is illustrated in figures 3 and 4 in which there is only one set of tongues 82, a first end 84 of which is fixed to the outer axial wall 26 by first connecting means 86 and a second end 88 is fixed to the inner axial wall 28 by means of second connecting means 90.
  • first and second connecting means are advantageously of the bolt type.
  • the tongue is further brazed (or welded) to the chamber bottom which may for example be formed by the single piece 80 of the aforementioned variant. This solder is of course made at the inter-injector spaces between the openings 32.
  • FIG 5 illustrates a second embodiment (see also the detail of Figure Sa) in which the seal between the outer axial wall 26 or inner 28 and the chamber bottom 30 is no longer provided by a "slats" type circular seal But by a split circular segment (open) 92; 94 mounted tight against the axial wall, provided with a sealing system and intended to cooperate with a circular groove 96; 98 of the metal ring 54, 56.
  • the clearance at the bottom of the groove 96 housing the outer segment 92 is calculated so that, in operation, the metal ring does not come into contact with the outer axial wall 26 of material composite, or with the inner face 92a of the segment 92.
  • the segment 94 of the inner wall is prestressed, the hot expansion of the chamber bottom having the effect of detaching the bottom of the inner wall.
  • the first end 42; 44 of the fastening tab 36; 38 is secured integrally and according to its location to one or the other of the outer axial walls 26 or inner 28 of the combustion chamber by the first attachment means 46; 48 and the second end 50; 52 is preferably attached by brazing or welding to the metal ring 54; 56, itself brazed or welded to the metal chamber bottom 30 of the combustion chamber.
  • the figure 6 illustrates a first variant embodiment of the aforementioned assembly wherein the chamber bottom and the metal crowns of the fixing tongues support form a single piece 100 on which will be soldered or soldered directly the second ends of these tabs 50; 52. This unique piece of course integrates the sealing means to previous segments.
  • a second variant is illustrated in figure 7 in which there is only one set of tongues 102, a first end 104 is fixed to the outer axial wall 26 by first connecting means 106 and a second end 108 is fixed to the inner axial wall 28 by second connecting means 110.
  • first and second fixing means are advantageously of the bolt type.
  • the tongue is further brazed (or welded) to the chamber bottom which may, for example, be formed by the single piece 100 of the aforementioned variant. This solder is of course made at the inter-injector spaces between the openings 32.

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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)
  • Fuel-Injection Apparatus (AREA)
  • Gasket Seals (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

Domaine de l'inventionField of the invention

La présente invention se rapporte au domaine spécifique des turbomachines et elle s'intéresse plus particulièrement au problème posé par le montage d'un fond métallique de chambre de combustion d'une turbomachine sur les parois en matériau composite de type CMC (composite à matrice céramique) de cette chambre. Une telle chambre de combustion est connue à partir de US 5 291 732 .The present invention relates to the specific field of turbomachines and is more particularly concerned with the problem posed by the mounting of a metal bottom of a combustion chamber of a turbomachine on the walls of composite material of the CMC type (ceramic matrix composite ) of this room. Such a combustion chamber is known from US 5,291,732 .

Art antérieurPrior art

Classiquement, dans un turboréacteur ou un turbopropulseur, la turbine haute pression, notamment son distributeur d'entrée (HPT nozzle), le système d'injection, la chambre de combustion ainsi que l'enveloppe annulaire de cette chambre sont réalisées dans des matériaux de type métallique. Cependant, dans certaines conditions particulières d'utilisation mettant en oeuvre des températures de combustion notablement élevées, l'emploi d'une chambre entièrement métallique s'avère d'un point de vue thermique totalement inadaptée et il doit être recouru à une chambre à base de matériaux composites haute température de type CMC. 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 et plus particulièrement à ses seules parois axiales, le distributeur d'entrée de la turbine haute pression, le système d'injection et l'enveloppe annulaire restant alors réalisées plus classiquement en des matériaux métalliques. Or, les matériaux métalliques et les matériaux composites ont des coefficients de dilatation thermique très différents. Il en résulte des problèmes particulièrement aigus notamment au niveau de la liaison entre les parois en matériau composite de la chambre de combustion et le fond de chambre métallique.Conventionally, in a turbojet engine or a turboprop engine, the high pressure turbine, in particular its inlet nozzle (HPT nozzle), the injection system, the combustion chamber and the annular envelope of this chamber are made of metal type. However, under certain particular conditions of use using significantly higher combustion temperatures, the use of an all-metal chamber is from a thermal point of view totally inadequate and it must be resorted to a chamber based on of high temperature composite materials of the CMC type. However, the difficulties of implementation and the cost of these materials mean that their use is most often limited to the combustion chamber itself and more particularly to its only axial walls, the inlet valve of the high pressure turbine, the injection system and the annular envelope then remaining more typically made of metal materials. However, metal materials and composite materials have very different coefficients of thermal expansion. This results in particularly acute problems especially at the level of the connection between the composite material walls of the combustion chamber and the metal chamber bottom.

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

La présente invention pallie ces inconvénients en proposant un montage de fond de chambre métallique ayant la capacité d'absorber les déplacements induits par les différences des coefficients de dilatation entre ce fond métallique et les parois en composite de la chambre de combustion.The present invention overcomes these disadvantages by proposing a metal chamber bottom assembly having the capacity to absorb the displacements induced by the differences in the coefficients of expansion between this metal bottom and the composite walls of the combustion chamber.

Ces buts sont atteints par une chambre de combustion annulaire comportant des parois axiales externe et interne en matériau composite et un fond de chambre en matériau métallique, caractérisée en ce que pour permettre une libre dilatation radiale dudit fond de chambre par rapport auxdites parois axiales, ledit fond de chambre est maintenu en position entre lesdites parois axiales par une pluralité de languettes souples fixées d'une part auxdites parois axiales par des moyens de fixation et d'autre part audit fond de chambre par brasure ou soudure, ledit fond de chambre comportant en outre des moyens pour assurer l'étanchéité entre ledit fond de chambre et lesdites parois axiales.These objects are achieved by an annular combustion chamber comprising outer and inner axial walls of composite material and a chamber bottom of metallic material, characterized in that to allow radial free expansion of said chamber bottom with respect to said axial walls, said chamber bottom is held in position between said axial walls by a plurality of flexible tongues fixed on the one hand to said axial walls by fixing means and on the other hand to said bottom chamber by soldering or welding, said chamber bottom comprising besides means for sealing between said chamber bottom and said axial walls.

Avec ce système de fixation à base de languettes souples, les dilatations du fond de chambre métallique sont absorbées sans détériorer les parois en matériau composite. En effet, les languettes peuvent reprendre les efforts dus à la forte dilatation du fond de chambre sans solliciter ces parois qui au contraire se dilatent peu.With this fastening system based on flexible tongues, the expansions of the metal chamber bottom are absorbed without damaging the walls of composite material. Indeed, the tongues can take the efforts due to the large expansion of the chamber floor without soliciting these walls which instead expand little.

Les languettes souples de fixation sont en un matériau métallique et les moyens de fixation sont constitués par une pluralité de boulons, de préférence à écrou prisonnier.The flexible fastening tabs are made of a metallic material and the fastening means consist of a plurality of bolts, preferably with a prison nut.

Selon un mode de réalisation, les moyens d'étanchéité comportent un joint circulaire de type « à lamelles » monté dans une gorge circulaire dudit fond de chambre métallique et destiné à assurer un appui sur ladite paroi axiale de la chambre de combustion en regard. De préférence, le joint circulaire d'étanchéité est sectorisé et il est maintenu en appui contre ladite paroi axiale au moyen d'un élément élastique fixé sur ledit fond de chambre métallique. Cet élément élastique est constitué par un ressort à lames.According to one embodiment, the sealing means comprise a "slat" type circular seal mounted in a circular groove of said metal chamber bottom and intended to provide a bearing on said axial wall of the combustion chamber opposite. Preferably, the circular seal is sectored and is held in abutment against said axial wall by means of a resilient element fixed on said metal chamber bottom. This elastic element is constituted by a leaf spring.

Selon un mode de réalisation alternatif, les moyens d'étanchéité comportent un segment circulaire monté contre ladite paroi axiale et destiné à coopérer avec une gorge circulaire dudit fond de chambre métallique. De préférence, ce segment circulaire d'étanchéité est fendu.According to an alternative embodiment, the sealing means comprise a circular segment mounted against said axial wall and intended to cooperate with a circular groove of said metal chamber bottom. Preferably, this circular sealing segment is split.

Selon un mode de réalisation avantageux, les languettes souples de fixation comportent une première extrémité fixée à l'une ou l'autre desdites parois axiales par lesdits moyens de fixation et une seconde extrémité fixée par brasure ou soudure audit fond de chambre. Dans ce cas, le fond de chambre peut comporter en outre une couronne métallique sur laquelle sont brasées ou soudées lesdites secondes extrémités desdites languettes souples de fixation.According to an advantageous embodiment, the flexible tongues of attachment comprise a first end fixed to one or the other of said axial walls by said fixing means and a second end fixed by soldering or welding to said chamber bottom. In this case, the chamber bottom may comprise in addition a metal ring on which are brazed or welded said second ends of said flexible fastening tongues.

Selon un autre mode de réalisation, les languettes souples de fixation comportent une première extrémité fixée à l'une desdites parois axiales par des premiers moyens de liaison une seconde extrémité fixée à l'autre desdites parois axiales par des seconds moyens de liaison et une partie centrale fixée au fond de chambre par brasure ou soudure. Avantageusement, ces languettes souples de fixation sont disposées entre chacune des buses d'injection.According to another embodiment, the flexible fastening tabs comprise a first end attached to one of said axial walls by first connecting means a second end attached to the other of said axial walls by second connecting means and a part central fixed to the bottom of the chamber by soldering or welding. Advantageously, these flexible fastening tabs are disposed between each of the injection nozzles.

Brève description des dessinsBrief description of the drawings

Les caractéristiques et avantages de la présente invention ressortiront mieux de la description suivante, faite à titre indicatif et non limitatif, en regard des dessins annexés sur lesquels :

  • la figure 1 est une vue schématique en demi-coupe axiale d'une partie d'injection d'une turbomachine incorporant un premier exemple de réalisation d'un assemblage selon l'invention,
  • la figure la montre un détail de l'assemblage de la figure 1,
  • la figure 2 est une vue schématique en demi-coupe axiale d'une partie d'injection d'une turbomachine incorporant une première variante du premier exemple de réalisation d'un assemblage selon l'invention,
  • la figure 3 est une vue schématique en demi-coupe axiale d'une partie d'injection d'une turbomachine incorporant une seconde variante du premier exemple d'assemblage selon l'invention,
  • la figure 4 est une partielle en bout illustrant la disposition alternée des buses d'injection et des languettes de fixation,
  • la figure 5 est une vue schématique en demi-coupe axiale d'une partie d'injection d'une turbomachine incorporant un second exemple de réalisation d'un assemblage selon l'invention,
  • la figure Sa montre un détail de l'assemblage de la figure 5,
  • la figure 6 est une vue schématique en demi-coupe axiale d'une partie d'injection d'une turbomachine incorporant une première variante du second exemple d'assemblage selon l'invention, et
  • la figure 7 est une vue schématique en demi-coupe axiale d'une partie d'injection d'une turbomachine incorporant une seconde variante du second exemple d'assemblage selon l'invention.
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:
  • the figure 1 is a schematic axial half-sectional view of an injection part of a turbomachine incorporating a first embodiment of an assembly according to the invention,
  • the figure shows a detail of the assembly of the figure 1 ,
  • the figure 2 is a schematic axial half-section view of an injection part of a turbomachine incorporating a first variant of the first embodiment of an assembly according to the invention,
  • the figure 3 is a schematic axial half-sectional view of an injection part of a turbomachine incorporating a second variant of the first assembly example according to the invention,
  • the figure 4 is a partial end illustrating the alternate arrangement of injection nozzles and fastening tabs,
  • the figure 5 is a schematic axial half-sectional view of an injection part of a turbomachine incorporating a second embodiment of an assembly according to the invention,
  • Figure Sa shows a detail of the assembly of the figure 5 ,
  • the figure 6 is a schematic axial half-sectional view of an injection part of a turbomachine incorporating a first variant of the second assembly example according to the invention, and
  • the figure 7 is a schematic axial half-sectional view of an injection part of a turbomachine incorporating a second variant of the second assembly example according to the invention.

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

La figure 1 montre en demi-coupe axiale une partie d'injection d'une turbomachine comprenant :

  • . une enveloppe annulaire externe (ou carter externe) 12, d'axe longitudinal 10,
  • . une enveloppe annulaire interne (ou carter interne) coaxiale 14,
  • . un espace annulaire 16 compris entre les deux enveloppes 12 et 14 recevant le comburant comprimé, généralement de l'air, provenant en amont d'un compresseur (non représenté) de la turbomachine, au travers d'un conduit annulaire de diffusion 18 (on notera la présence de la grille de diffusion 18a) définissant un flux général F d'écoulement des gaz,
    cet espace 16 comportant, dans le sens d'écoulement des gaz, tout d'abord un ensemble d'injection formé d'une pluralité de systèmes d'injection 20 régulièrement répartis autour du conduit 18 et comportant chacun une buse d'injection de carburant 22 fixée sur l'enveloppe annulaire externe 12 (dans un souci de simplification des dessins les mélangeur et déflecteur associés à chaque buse d'injection ont été omis), ensuite une chambre de combustion annulaire 24, formée d'une paroi axiale externe 26 et d'une paroi axiale interne 28, toutes deux coaxiales d'axe 10 et réalisées en un matériau composite haute température, de type CMC ou autres (carbone par exemple), et d'une paroi transversale 30 réalisée en un matériau métallique, formant fond de chambre, et pourvue d'ouvertures 32 pour la fixation du système d'injection, et enfin un distributeur annulaire (non représenté) formant un étage d'entrée d'une turbine haute pression. Dans la réalisation illustrée, on notera la présence de la casquette interne 33 prolongeant vers l'amont (par rapport au flux F) la paroi interne 28 de la chambre de combustion. Une casquette externe 34 peut par contre être directement intégrée à la paroi externe 26 de cette chambre de combustion.
The figure 1 shows in axial half-section an injection part of a turbomachine comprising:
  • . an outer annular casing (or outer casing) 12, of longitudinal axis 10,
  • . an inner annular envelope (or inner casing) coaxial 14,
  • . an annular space 16 between the two envelopes 12 and 14 receiving the compressed oxidant, generally air, coming upstream of a compressor (not shown) of the turbomachine, through an annular diffusion duct 18 (on note the presence of the diffusion gate 18a) defining a general flow F of gas flow,
    this space 16 comprising, in the 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 the outer annular casing 12 (for the sake of simplification of the drawings the mixer and deflector associated with each injection nozzle have been omitted), then an annular combustion chamber 24, formed of an outer axial wall 26 and an inner axial wall 28, both coaxial axis 10 and made of a high temperature composite material, CMC type or other (carbon for example), and a transverse wall 30 made of a metallic material, forming a bottom chamber, and provided with openings 32 for fixing the injection system, and finally an annular distributor (not shown) forming an inlet stage of a high pressure turbine. In the illustrated embodiment, note the presence of the inner cap 33 extending upstream (with respect to the flow F) the inner wall 28 of the combustion chamber. An outer cap 34 may instead be directly integrated with the outer wall 26 of the combustion chamber.

Selon l'invention, le fond métallique 30 de la chambre de combustion qui a un coefficient de dilatation thermique très différent de celui des parois axiales externe 26 et interne 28 en matériau composite de la chambre de combustion, est maintenu fixement en position entre ces parois axiales par une pluralité de languettes souples 36, 38 régulièrement réparties entre les buses d'injection de carburant 22 (voir par exemple la figure 4). Ces languettes de fixation sont montées pour une première série d'entre elles (voir la languette référencée 36) entre le fond métallique 30 et la paroi axiale externe 26 et pour une seconde série d'entre elles (voir la languette référencée 38) entre le fond métallique 30 et la paroi axiale interne 28. Chaque languette de fixation souple est réalisée en un matériau métallique et est constituée de préférence d'une mince lame, de largeur constante ou non, ayant un point d'attache à chacune de ses deux extrémités.According to the invention, the metal bottom 30 of the combustion chamber which has a coefficient of thermal expansion very different from that of the axial walls outer 26 and inner 28 of composite material of the combustion chamber, is fixedly held in position between these axial walls by a plurality of flexible tabs 36, 38 regularly distributed between the fuel injection nozzles 22 (see for example the figure 4 ). These fixing tabs are mounted for a first series of them (see the tab referenced 36) between the metal bottom 30 and the outer axial wall 26 and for a second series of them (see the tab referenced 38) between the metal base 30 and the inner axial wall 28. Each flexible fastening tongue is made of a metallic material and is preferably constituted by a thin blade, of constant width or not, having a point of attachment at each of its two ends. .

Selon un premier exemple de réalisation illustré à la figure 1 (voir aussi le détail de la figure lA), la première extrémité 42 ; 44 de la languette de fixation est fixée solidairement et selon son emplacement à l'une ou l'autre des parois axiales externe 26 ou interne 28 de la chambre de combustion par des premiers moyens de fixation 46 ; 48 et la seconde extrémité 50 ; 52 est fixée de préférence par soudure ou brasure à une couronne métallique 54 ; 56, elle-même brasée ou soudée sur le fond de chambre métallique 30 de la chambre de combustion. Cet accrochage permet d'absorber les dilatations du fond de chambre sans détériorer les parois axiales en composite qui se déplacent peu radialement.According to a first exemplary embodiment illustrated in figure 1 (see also the detail of FIG. 1A), the first end 42; 44 of the fastening tongue is fixed integrally and according to its location at one or the other of the outer axial walls 26 or inner 28 of the combustion chamber by first fixing means 46; 48 and the second end 50; 52 is preferably fixed by welding or brazing to a metal ring 54; 56, itself brazed or welded to the metal chamber bottom 30 of the combustion chamber. This attachment absorbs the dilatations of the chamber bottom without damaging the composite axial walls that move little radially.

Les premiers moyens de fixation disposés en position décalée par rapport aux buses d'injection sont avantageusement de type boulons. Et, pour en faciliter l'accès ainsi que le montage/démontage, ces boulons sont choisis de préférence du type à écrou prisonnier.The first fastening means disposed offset from the injection nozzles are advantageously bolt type. And, to facilitate access and assembly / disassembly, these bolts are preferably chosen to type prison nut.

L'étanchéité entre la paroi axiale externe ou interne et la couronne métallique est assurée par un joint circulaire de type « à lamelles » 58 ; 60 monté dans une gorge circulaire 62 ; 64 de la couronne métallique. Ce joint d'étanchéité avantageusement sectorisé comporte dans sa partie amont un béquet 66 ; 68 destiné à assurer un appui torique sur la paroi axiale en regard 26 ; 28 de la chambre de combustion. Le joint est plaqué contre la paroi par un élément élastique 70 ; 72, de préférence un ressort à lames, et maintenu en position par une pluralité de pions 74 ; 76 solidaires de la couronne. On notera que le jeu existant entre le bord périphérique externe 78 du fond de chambre (et le bord correspondant de la couronne métallique) est calculé de façon à ce que, en fonctionnement, la couronne métallique ne vienne pas comprimer la paroi axiale externe 26 en matériau composite ou simplement ne vienne à son contact. De même, on notera que le joint 60 assurant l'étanchéité avec la paroi axiale interne 28 est précontraint, la dilatation à chaud du fond de chambre ayant pour effet de décoller ce fond de la paroi interne.The seal between the outer or inner axial wall and the metal ring is provided by a "slat" type circular seal 58; 60 mounted in a circular groove 62; 64 of the metal crown. This advantageously sectored seal comprises in its upstream part a spigot 66; 68 for providing an O-bearing on the facing axial wall 26; 28 of the combustion chamber. The seal is pressed against the wall by an elastic member 70; 72, preferably a leaf spring, and held in position by a plurality of pins 74; 76 integral with the crown. Note that the clearance between the outer peripheral edge 78 of the chamber floor (and the edge corresponding of the metal ring) is calculated so that, in operation, the metal ring does not come to compress the outer axial wall 26 of composite material or simply does not come into contact with it. Similarly, it will be noted that the seal 60 sealing with the inner axial wall 28 is prestressed, the hot expansion of the chamber bottom having the effect of detaching the bottom of the inner wall.

La figure 2 illustre une première variante de réalisation de l'accrochage du fond de chambre métallique sur les parois axiales en matériau composite de la chambre de combustion, dans laquelle ce fond de chambre et les couronnes métalliques de support des languettes de fixation ne forment qu'une seule pièce 80 sur laquelle seront brasées ou soudées directement les secondes extrémités des languettes 50 ; 52. Cette pièce unique intègre bien entendu les moyens d'étanchéité précédents.The figure 2 illustrates a first variant embodiment of the attachment of the metal chamber bottom to the axial walls made of composite material of the combustion chamber, in which the chamber bottom and the metal crowns of the fixing tongues form a single piece 80 on which will be soldered or soldered directly the second ends of the tabs 50; 52. This unique piece of course incorporates the previous sealing means.

Une seconde variante est illustrée aux figures 3 et 4 dans lesquelles il n'existe plus qu'une seule série de languettes 82 dont une première extrémité 84 est fixée à la paroi axiale externe 26 par des premiers moyens de liaison 86 et une seconde extrémité 88 est fixée à la paroi axiale interne 28 par des seconds moyens de liaison 90. Ces premiers et seconds moyens de liaison sont avantageusement de type boulons. La languette est en outre brasée (ou soudée) sur le fond de chambre qui peut par exemple être formé par la pièce unique 80 de la variante précitée. Cette brasure est bien entendue effectuée au niveau des espaces inter-injecteurs entre les ouvertures 32.A second variant is illustrated in figures 3 and 4 in which there is only one set of tongues 82, a first end 84 of which is fixed to the outer axial wall 26 by first connecting means 86 and a second end 88 is fixed to the inner axial wall 28 by means of second connecting means 90. These first and second connecting means are advantageously of the bolt type. The tongue is further brazed (or welded) to the chamber bottom which may for example be formed by the single piece 80 of the aforementioned variant. This solder is of course made at the inter-injector spaces between the openings 32.

La figure 5 illustre un second exemple de réalisation (voir aussi le détail de la figure Sa) dans lequel l'étanchéité entre la paroi axiale externe 26 ou interne 28 et le fond de chambre 30 n'est plus assurée par un joint circulaire de type « à lamelles » mais par un segment circulaire fendu (ouvert) 92 ; 94 monté serré contre la paroi axiale, muni d'un système couvre-joint et destiné à coopérer avec une gorge circulaire 96 ; 98 de la couronne métallique 54, 56. le jeu au fond de la gorge 96 de logement du segment externe 92 est calculé de façon à ce que, en fonctionnement, la couronne métallique ne vienne en contact ni avec la paroi axiale externe 26 en matériau composite, ni avec la face interne 92a du segment 92. De même, le segment 94 de la paroi interne est précontraint, la dilatation à chaud du fond de chambre ayant pour effet de décoller ce fond de la paroi interne.The figure 5 illustrates a second embodiment (see also the detail of Figure Sa) in which the seal between the outer axial wall 26 or inner 28 and the chamber bottom 30 is no longer provided by a "slats" type circular seal But by a split circular segment (open) 92; 94 mounted tight against the axial wall, provided with a sealing system and intended to cooperate with a circular groove 96; 98 of the metal ring 54, 56. the clearance at the bottom of the groove 96 housing the outer segment 92 is calculated so that, in operation, the metal ring does not come into contact with the outer axial wall 26 of material composite, or with the inner face 92a of the segment 92. Similarly, the segment 94 of the inner wall is prestressed, the hot expansion of the chamber bottom having the effect of detaching the bottom of the inner wall.

Pour le reste, et comme dans le premier exemple de réalisation, la première extrémité 42 ; 44 de la languette de fixation 36 ; 38 est fixée solidairement et selon son emplacement à l'une ou l'autre des parois axiales externe 26 ou interne 28 de la chambre de combustion par les premiers moyens de fixation 46 ; 48 et la seconde extrémité 50 ; 52 est fixée de préférence par brasure ou soudure à la couronne métallique 54 ; 56, elle-même brasée ou soudée sur le fond de chambre métallique 30 de la chambre de combustion.For the rest, and as in the first embodiment, the first end 42; 44 of the fastening tab 36; 38 is secured integrally and according to its location to one or the other of the outer axial walls 26 or inner 28 of the combustion chamber by the first attachment means 46; 48 and the second end 50; 52 is preferably attached by brazing or welding to the metal ring 54; 56, itself brazed or welded to the metal chamber bottom 30 of the combustion chamber.

La figure 6 illustre une première variante de réalisation du montage précité dans lequel le fond de chambre et les couronnes métalliques de support des languettes de fixation ne forment plus qu'une seule pièce 100 sur laquelle seront brasées ou soudées directement les secondes extrémités de ces languettes 50 ; 52. Cette pièce unique intègre bien entendu les moyens d'étanchéité à segments précédents.The figure 6 illustrates a first variant embodiment of the aforementioned assembly wherein the chamber bottom and the metal crowns of the fixing tongues support form a single piece 100 on which will be soldered or soldered directly the second ends of these tabs 50; 52. This unique piece of course integrates the sealing means to previous segments.

Une seconde variante est illustrée à la figure 7 dans laquelle il n'existe plus qu'une seule série de languettes 102 dont une première extrémité 104 est fixée à la paroi axiale externe 26 par des premiers moyens de liaison 106 et une seconde extrémité 108 est fixée à la paroi axiale interne 28 par des seconds moyens de liaison 110. Ces premiers et seconds moyens de fixation sont avantageusement de type boulons. La languette est en outre brasée (ou soudée) sur le fond de chambre qui peut, par exemple, être formé par la pièce unique 100 de la variante précitée. Cette brasure est bien entendue effectuée au niveau des espaces inter-injecteurs entre les ouvertures 32.A second variant is illustrated in figure 7 in which there is only one set of tongues 102, a first end 104 is fixed to the outer axial wall 26 by first connecting means 106 and a second end 108 is fixed to the inner axial wall 28 by second connecting means 110. These first and second fixing means are advantageously of the bolt type. The tongue is further brazed (or welded) to the chamber bottom which may, for example, be formed by the single piece 100 of the aforementioned variant. This solder is of course made at the inter-injector spaces between the openings 32.

Claims (13)

  1. An annular combustion chamber (24) having outer (26) and inner (28) axially-extending side walls (26, 28) of composite material and an end wall (30, 80, 100) of metal material, the chamber being characterized in that in order to enable said end wall to expand freely in a radial direction relative to said side walls, said end wall is held in position between said inner and outer side walls by a plurality of flexible tongues (36, 38; 82; 102) fixed firstly to said side walls by fixing means (46, 48; 86, 90; 106, 110) and secondly to said end wall by brazing or welding, said end wall further including means (58, 60; 92, 94) for providing sealing between said end wall and said side walls.
  2. A combustion chamber according to claim 1,
    characterized in that said flexible fixing tongues are made of a metal material.
  3. A combustion chamber according to claim 1,
    characterized in that said fixing means are constituted by a plurality of bolts, preferably having captive nuts.
  4. A combustion chamber according to claim 1,
    characterized in that said sealing means comprise a "spring blade" type circular gasket (58, 60) moulted in a circular groove (62, 64) of said metal end wall and designed to press against the facing one of said side walls (26, 28) of the combustion chamber.
  5. A combustion chamber according to claim 4,
    characterized in that said circular sealing gasket is subdivided into sectors.
  6. A combustion chamber according to claim 4,
    characterized in that said circular sealing gasket is held pressed against said side wall by means of a resilient element (70, 72) fixed to said metal end wall of the chamber.
  7. A combustion chamber according to claim 6,
    characterized in that said resilient element is constituted by spring blades.
  8. A combustion chamber according to claim 1,
    characterized in that said sealing means comprise a circular segment (92, 94) mounted against said side wall and designed two co-operate with a circular groove (96, 98) of said metal end wall.
  9. A combustion chamber according to claim 8,
    characterized in that said circular sealing segment is split.
  10. A combustion chamber according to claim 1,
    characterized in that each of said flexibly fixing tongues (36, 38) has a first end (42, 44) fixed to one or the other of said side walls by said fixing means, and a second end (50, 52) fixed to said end wall by brazing or welding.
  11. A combustion chamber according to claim 10,
    characterized in that said end wall further comprises a metal ring (54, 56) having said second ends of said flexible fixing tongues brazed or welded thereto.
  12. A combustion chamber according to claim 1,
    characterized in that each flexible fixing tongue (82, 102) has a first end (84, 104) fixed to one of said side walls by first convection means (86, 106), a second end (88, 108) fixed to the other one of said side walls by second connection means (90, 110), and a central potion fixed to the end wall (80, 100) by brazing or welding.
  13. A combustion chamber according to claim 12,
    characterized in that said flexible fixing tongues are disposed between successive injection nozzles (22).
EP02291362A 2001-06-06 2002-06-04 Combustion chamber with a system for mounting the chamber end wall Expired - Lifetime EP1265033B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0107368A FR2825779B1 (en) 2001-06-06 2001-06-06 COMBUSTION CHAMBER EQUIPPED WITH A CHAMBER BOTTOM FIXING SYSTEM
FR0107368 2001-06-06

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EP1265033A1 EP1265033A1 (en) 2002-12-11
EP1265033B1 true EP1265033B1 (en) 2008-10-22

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EP (1) EP1265033B1 (en)
JP (1) JP3967633B2 (en)
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FR (1) FR2825779B1 (en)

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DE60229464D1 (en) 2008-12-04
EP1265033A1 (en) 2002-12-11
FR2825779B1 (en) 2003-08-29
JP3967633B2 (en) 2007-08-29
US6647729B2 (en) 2003-11-18
JP2002372241A (en) 2002-12-26
US20020184887A1 (en) 2002-12-12
FR2825779A1 (en) 2002-12-13

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