EP1717516B1 - Easily disassembled combustion chamber with improved aerodynamic performance - Google Patents

Easily disassembled combustion chamber with improved aerodynamic performance Download PDF

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Publication number
EP1717516B1
EP1717516B1 EP06112766.8A EP06112766A EP1717516B1 EP 1717516 B1 EP1717516 B1 EP 1717516B1 EP 06112766 A EP06112766 A EP 06112766A EP 1717516 B1 EP1717516 B1 EP 1717516B1
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EP
European Patent Office
Prior art keywords
combustion chamber
tongues
wall
annular
end wall
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EP06112766.8A
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German (de)
French (fr)
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EP1717516A1 (en
Inventor
Christophe Pieussergues
Pierre Sablayrolles
Laurent Marnas
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • 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
    • F23R3/002—Wall structures
    • 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
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00017—Assembling combustion chamber liners or subparts

Definitions

  • the invention relates to a combustion chamber for a reactor. It relates more particularly to an improvement in the assembly of the different parts of the combustion chamber, with the dual aim of reducing the disturbances of the air flow around it, which may penalize its performance, and to facilitate the maintenance.
  • a known combustion chamber is a divisible assembly of several parts. There is a generally annular outer wall, a generally annular inner wall and a bottom wall extending between said outer and inner walls.
  • the fuel injection means are mounted on said bottom wall of the chamber. They consist of a plurality of injection systems spaced circularly.
  • a fairing defines with said bottom wall of chamber an annular cavity housing these injection means.
  • the combustion chamber thus defined is an axisymmetric assembly which must be as aerodynamic as possible since placed in the air stream.
  • the shroud generally comprises an annular piece called outer cap and an annular piece called inner cap. The various components of the combustion chamber are assembled together removably.
  • the bolting assembly is replaced by a set of welds between said inner and outer walls, the bottom wall of the chamber and the fairing.
  • this type of combustion chamber there are no more screw heads to disturb the flow at the external bypass or at the internal bypass of the combustion chamber.
  • the welds make this combustion chamber difficult to repair because it is necessary at least to cut said chamber according to two circular welds. As these welds are on cones, it is very difficult and expensive to reassemble the chamber after repairing an element thereof.
  • the document EP1265033 A1 discloses all the features of the preamble of claim 1.
  • the invention overcomes this double difficulty.
  • the invention relates to a combustion chamber of a reactor comprising a generally annular outer wall, a generally annular inner wall, a chamber bottom wall extending between said outer and inner walls and on which are mounted means injection molding and a shroud defining with said bottom wall of an annular chamber chamber housing said injection means, said fairing comprising an annular piece said outer cap and an annular piece called inner cap, characterized in that said caps comprise parts internal fasteners projecting into said annular cavity, in that said bottom wall of the chamber comprises corresponding internal fasteners protruding inside said annular cavity and in that the fasteners of said caps. are assembled to the fasteners of said bottom wall of room.
  • the aforementioned internal fasteners are tabs distributed circumferentially or, more generally, ferrules.
  • those of said caps and those of said bottom wall of the chamber are welded.
  • they are welded two by two together at their ends only.
  • a possible disassembly of the components of the combustion chamber can be easily done by grinding the ends of the tongues so as to eliminate the welded areas.
  • fasteners are ferrules
  • said outer cap and said outer wall are assembled circumferentially by welding.
  • the welding can be done singing against singing.
  • the inner wall and the bottom wall of the chamber are secured circumferentially.
  • the assembly can be achieved by riveting or even capping.
  • the weld joining the tongues together is preferably a TIG weld, known per se.
  • a high intensity current passes through a tungsten electrode forming an arc with the parts to be assembled.
  • the metal receiving the arc undergoes a local fusion.
  • the welding is done in a neutral gas environment (argon for example).
  • the tongues carried by the caps are preferably assembled to them by brazing.
  • Each tab is assembled to the cap by means of a filler metal whose melting point is less than the melting point of the materials to be assembled. The assembly is performed without melting the metal of the elements to be assembled. Once brought to the melting temperature, the filler metal enters by capillary attraction between the parts to be assembled.
  • the filler metal is preferably based on nickel for a brazing temperature of the order of 1160 ° C.
  • the inner cap has an annular band in contact enveloping with the end portion of the inner wall.
  • a combustion chamber 11 which consists of the assembly of several annular parts.
  • a combustion chamber 11 which consists of the assembly of several annular parts.
  • the shroud defines with said bottom wall of a chamber annular cavity 20 housing the means injection.
  • injectors 22 circumferentially spaced regularly and mounted on the bottom wall of chamber 14.
  • the invention relates more particularly to the method of assembly between said inner and outer walls, the bottom wall of the chamber and the two caps.
  • the caps 16, 17 comprise tongues 24, 25, respectively, projecting inside the annular cavity 20. These tongues are regularly distributed circumferentially.
  • Each cap has as many tabs 24 or 25 as there are injectors but they are offset circumferentially relative to the injectors for better accessibility in case of disassembly.
  • a tongue 24 or 25 has a curved portion 28 conforming to the shape of the inner face of the cap and a portion 29 curved radially inward, which protrudes into the annular cavity.
  • the bottom wall of the chamber also has tabs 34, 35 projecting into the annular cavity.
  • the chamber bottom wall 14 and the tongues 34, 35 carried by it, inside and outside, are drawn from the same cut and stamped sheet as can be seen on FIG. figure 2 .
  • outer tongues 34 and a series of inner tongues 35 There are a series of outer tongues 34 and a series of inner tongues 35.
  • the outer tongues 34 of the chamber bottom wall and the tongues 24 of the outer cap are equal in number and correspond, each tongue of the cap being applied. by its projecting portion against a corresponding tongue of the chamber bottom wall.
  • the tongues 25 of the inner cap and the inner tongues 35 of the bottom wall of the chamber are equal in number and correspond, each tongue of the inner cap being applied by its projecting portion against the corresponding tongue of the wall of the bedroom background.
  • the tongues of said caps are assembled to the tongues of said bottom wall of the chamber. More particularly, the tongues of said caps and those of said chamber bottom wall are welded in pairs and preferably only at their ends.
  • the solder 40 is preferably of the TIG type.
  • the parts of the tongues 24, 25 secured to the caps 16, 17 are joined thereto by brazing. Because the tongues are bent so as to be placed side by side in pairs and welded only at their ends, it is relatively easy to separate them, for example by grinding said welded ends. . These grinding operations will disassemble the various parts of the combustion chamber for repairs. After these repairs reassembly is possible by re-welding the ends of the slightly shortened tabs 24, 34 and 25, 35.
  • outer cap 16 and said outer wall 12 are joined circumferentially by welding. As shown, the weld 42 is edge-to-edge so that the flow of air outside the combustion chamber is not disturbed.
  • the chamber bottom wall 14 is not attached to said outer part.
  • the inner wall 13 and said bottom wall chamber 14 are secured circumferentially.
  • the two walls are shaped with annular bands 43, 44 in contact. These strips can be secured by riveting or capping.
  • Said inner cap 17 also comprises an annular band 47 in contact enveloping with the annular band of said inner wall. It is not attached to this inner wall. This arrangement does not substantially disturb the flow of air within the vein defined by the inner wall and the inner cap of the combustion chamber. Said inner wall 13 and the inner cap 17 are not secured in their contact zone.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Cylinder Crankcases Of Internal Combustion Engines (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Portable Nailing Machines And Staplers (AREA)

Description

L'invention se rapporte à une chambre de combustion pour un réacteur. Elle concerne plus particulièrement un perfectionnement de l'assemblage des différentes parties de la chambre de combustion, dans le double but de réduire les perturbations de l'écoulement d'air autour de celle-ci, susceptible de pénaliser ses performances, et de faciliter la maintenance.The invention relates to a combustion chamber for a reactor. It relates more particularly to an improvement in the assembly of the different parts of the combustion chamber, with the dual aim of reducing the disturbances of the air flow around it, which may penalize its performance, and to facilitate the maintenance.

Une chambre de combustion connue est un assemblage divisible de plusieurs parties. On distingue une paroi extérieure globalement annulaire, une paroi intérieure globalement annulaire et une paroi de fond de chambre s'étendant entre lesdites parois extérieure et intérieure. Les moyens d'injection de carburant sont montés sur ladite paroi de fond de chambre. Ils sont constitués par une pluralité de systèmes d'injection espacés circulairement. En outre, un carénage définit avec ladite paroi de fond de chambre une cavité annulaire abritant ces moyens d'injection. La chambre de combustion ainsi définie constitue un ensemble axisymétrique qui doit être aussi aérodynamique que possible puisque placé dans la veine d'air. Le carénage comprend généralement une pièce annulaire dite casquette externe et une pièce annulaire dite casquette interne. Les différents éléments constitutifs de la chambre de combustion sont assemblés entre eux de façon démontable. Par exemple, il est connu d'assembler lesdites parois externe et interne, ladite paroi de fond de chambre et les éléments du carénage par une couronne de boulons agencée au voisinage de la paroi de fond de chambre. Les têtes de boulons perturbent l'écoulement de l'air. Cette perturbation pénalise les performances de la chambre de combustion.A known combustion chamber is a divisible assembly of several parts. There is a generally annular outer wall, a generally annular inner wall and a bottom wall extending between said outer and inner walls. The fuel injection means are mounted on said bottom wall of the chamber. They consist of a plurality of injection systems spaced circularly. In addition, a fairing defines with said bottom wall of chamber an annular cavity housing these injection means. The combustion chamber thus defined is an axisymmetric assembly which must be as aerodynamic as possible since placed in the air stream. The shroud generally comprises an annular piece called outer cap and an annular piece called inner cap. The various components of the combustion chamber are assembled together removably. For example, it is known to assemble said outer and inner walls, said bottom wall of the chamber and the elements of the fairing by a bolt ring arranged in the vicinity of the bottom wall of the chamber. Bolt heads disturb the flow of air. This disturbance penalizes the performance of the combustion chamber.

Dans certaines chambres de combustion, le montage par boulonnage est remplacé par un ensemble de soudures entre lesdites parois intérieure et extérieure, la paroi du fond de chambre et le carénage. Dans ce type de chambre de combustion, il n'y a plus de têtes de vis pour perturber l'écoulement au niveau du contournement externe ou au niveau du contournement interne de la chambre de combustion. En revanche, les soudures rendent cette chambre de combustion difficile à réparer car il faut au moins découper ladite chambre suivant deux soudures circulaires. Comme ces soudures se trouvent sur des cônes, il est très difficile et coûteux de réassembler la chambre après réparation d'un élément de celle-ci. Le document EP1265033 A1 divulgue toutes les caractéristiques du préambule de la revendication 1.In some combustion chambers, the bolting assembly is replaced by a set of welds between said inner and outer walls, the bottom wall of the chamber and the fairing. In this type of combustion chamber, there are no more screw heads to disturb the flow at the external bypass or at the internal bypass of the combustion chamber. On the other hand, the welds make this combustion chamber difficult to repair because it is necessary at least to cut said chamber according to two circular welds. As these welds are on cones, it is very difficult and expensive to reassemble the chamber after repairing an element thereof. The document EP1265033 A1 discloses all the features of the preamble of claim 1.

L'invention permet de surmonter cette double difficulté.The invention overcomes this double difficulty.

Plus précisément, l'invention concerne une chambre de combustion d'un réacteur comprenant une paroi extérieure globalement annulaire, une paroi intérieure globalement annulaire, une paroi de fond de chambre s'étendant entre lesdites parois extérieure et intérieure et sur laquelle sont montés des moyens d'injection et un carénage définissant avec ladite paroi de fond de chambre une cavité annulaire abritant lesdits moyens d'injection, ledit carénage comprenant une pièce annulaire dite casquette externe et une pièce annulaire dite casquette interne, caractérisée en ce que lesdites casquettes comportent des pièces de fixation internes faisant saillie à l'intérieur de ladite cavité annulaire, en ce que ladite paroi de fond de chambre comprend des pièces de fixation internes correspondantes faisant saillie à l'intérieur de ladite cavité annulaire et en ce que les pièces de fixation desdites casquettes sont assemblées aux pièces de fixation de ladite paroi de fond de chambre.More specifically, the invention relates to a combustion chamber of a reactor comprising a generally annular outer wall, a generally annular inner wall, a chamber bottom wall extending between said outer and inner walls and on which are mounted means injection molding and a shroud defining with said bottom wall of an annular chamber chamber housing said injection means, said fairing comprising an annular piece said outer cap and an annular piece called inner cap, characterized in that said caps comprise parts internal fasteners projecting into said annular cavity, in that said bottom wall of the chamber comprises corresponding internal fasteners protruding inside said annular cavity and in that the fasteners of said caps. are assembled to the fasteners of said bottom wall of room.

Les pièces de fixation internes précitées sont des languettes réparties circonférentiellement ou, plus globalement, des viroles.The aforementioned internal fasteners are tabs distributed circumferentially or, more generally, ferrules.

Par exemple, si on utilise des languettes, celles desdites casquettes et celles de ladite paroi de fond de chambre sont soudées. De préférence, elles sont soudées deux à deux entre elles à leurs extrémités seulement. Dans ces conditions, un éventuel démontage des éléments constitutifs de la chambre de combustion peut se faire facilement en meulant les extrémités des languettes de façon à éliminer les zones soudées.For example, if tongues are used, those of said caps and those of said bottom wall of the chamber are welded. Preferably, they are welded two by two together at their ends only. Under these conditions, a possible disassembly of the components of the combustion chamber can be easily done by grinding the ends of the tongues so as to eliminate the welded areas.

La séparation des languettes permet de diviser la chambre de combustion en plusieurs parties, rendant possible les réparations sur n'importe laquelle de ces parties.Separating the tabs divides the combustion chamber into several parts, making repairs to any of these parts possible.

Si les pièces de fixation sont des viroles, il est avantageux de conserver un assemblage sectorisé, comme s'il s'agissait de languettes, par exemple en réalisant une pluralité de soudures régulièrement réparties circonférentiellement. On peut combiner viroles et languettes.If the fasteners are ferrules, it is advantageous to maintain a sectorized assembly, as if it were tongues, for example by producing a plurality of welds regularly distributed circumferentially. We can combine ferrules and tongues.

Selon un mode de réalisation avantageux, ladite casquette externe et ladite paroi extérieure sont assemblées circonférentiellement par soudage. La soudure peut être faite chant contre chant.According to an advantageous embodiment, said outer cap and said outer wall are assembled circumferentially by welding. The welding can be done singing against singing.

Avantageusement, la paroi intérieure et la paroi de fond de chambre sont solidarisées circonférentiellement. L'assemblage peut être réalisé par rivetage ou même bouchonnage.Advantageously, the inner wall and the bottom wall of the chamber are secured circumferentially. The assembly can be achieved by riveting or even capping.

La soudure réunissant les languettes entre elles est de préférence une soudure de type TIG, connue en soi. Un courant de forte intensité passe par une électrode de tungstène en formant avec les pièces à assembler un arc électrique. Le métal recevant l'arc subit une fusion locale. La soudure se fait dans un environnement de gaz neutre (argon par exemple).The weld joining the tongues together is preferably a TIG weld, known per se. A high intensity current passes through a tungsten electrode forming an arc with the parts to be assembled. The metal receiving the arc undergoes a local fusion. The welding is done in a neutral gas environment (argon for example).

Les languettes portées par les casquettes sont de préférence assemblées à celles-ci par brasage. On assemble chaque languette à la casquette par l'intermédiaire d'un métal d'apport dont le point de fusion est inférieur au point de fusion des matériaux à assembler. L'assemblage est donc effectué sans faire fondre le métal des éléments à assembler. Une fois porté à la température de fusion, le métal d'apport pénètre par attraction capillaire entre les parties à assembler. Le métal d'apport est de préférence à base de nickel pour une température de brasage de l'ordre de 1160°C.The tongues carried by the caps are preferably assembled to them by brazing. Each tab is assembled to the cap by means of a filler metal whose melting point is less than the melting point of the materials to be assembled. The assembly is performed without melting the metal of the elements to be assembled. Once brought to the melting temperature, the filler metal enters by capillary attraction between the parts to be assembled. The filler metal is preferably based on nickel for a brazing temperature of the order of 1160 ° C.

Selon encore une autre caractéristique optionnelle, la casquette interne comporte une bande annulaire en contact enveloppant avec la partie d'extrémité de la paroi intérieure.According to yet another optional feature, the inner cap has an annular band in contact enveloping with the end portion of the inner wall.

L'invention sera mieux comprise et d'autres avantages de celle-ci apparaîtront plus clairement à la lumière de la description qui va suivre, donnée uniquement à titre d'exemple et faite en référence aux dessins annexés dans lesquels :

  • la figure 1 est une vue partielle en perspective d'une chambre de combustion conforme à l'invention ;
  • la figure 2 est une vue analogue à la figure 1 dans laquelle les moyens d'injection ont été enlevés pour mieux montrer l'assemblage des différentes parties constitutives de la chambre de combustion ; et
  • la figure 3 est une section radiale à plus grande échelle de la figure 2.
The invention will be better understood and other advantages thereof will appear more clearly in the light of the description which follows, given solely by way of example and with reference to the appended drawings in which:
  • the figure 1 is a partial perspective view of a combustion chamber according to the invention;
  • the figure 2 is a view similar to the figure 1 wherein the injection means have been removed to better show the assembly of the various constituent parts of the combustion chamber; and
  • the figure 3 is a radial section on a larger scale of the figure 2 .

Sur les dessins, on a représenté partiellement la partie avant d'une chambre de combustion 11, qui est constituée de l'assemblage de plusieurs pièces annulaires. On distingue une paroi extérieure 12 globalement annulaire, une paroi intérieure 13 globalement annulaire, une paroi de fond de chambre 14 s'étendant entre lesdites parois extérieure et intérieure et sur laquelle sont montés les moyens d'injection 21 et un carénage 15 comprenant une pièce annulaire dite casquette externe 16 et une pièce annulaire dite casquette interne 17. Le carénage définit avec ladite paroi de fond de chambre une cavité annulaire 20 abritant les moyens d'injection. Ceux-ci sont constitués d'une pluralité d'injecteurs 22 régulièrement espacés circonférentiellement et montés sur la paroi de fond de chambre 14.In the drawings, there is shown partially the front part of a combustion chamber 11, which consists of the assembly of several annular parts. There is a generally annular outer wall 12, a generally annular inner wall 13, a chamber bottom wall 14 extending between said outer walls and inside and on which are mounted the injection means 21 and a shroud 15 comprising an annular piece called said outer cap 16 and an annular piece said inner cap 17. The shroud defines with said bottom wall of a chamber annular cavity 20 housing the means injection. These consist of a plurality of injectors 22 circumferentially spaced regularly and mounted on the bottom wall of chamber 14.

L'invention concerne plus particulièrement le mode d'assemblage entre lesdites parois intérieure et extérieure, la paroi de fond de chambre et les deux casquettes.The invention relates more particularly to the method of assembly between said inner and outer walls, the bottom wall of the chamber and the two caps.

Plus particulièrement, les casquettes 16, 17 comportent des languettes 24, 25, respectivement, faisant saillie à l'intérieur de la cavité annulaire 20. Ces languettes sont régulièrement réparties circonférentiellement. Chaque casquette comporte autant de languettes 24 ou 25 qu'il y a d'injecteurs mais elles sont décalées circonférentiellement par rapport aux injecteurs, pour une meilleure accessibilité en cas de démontage. Une languette 24 ou 25 comporte une partie courbe 28 épousant la forme de la face intérieure de la casquette et une partie 29 recourbée radialement vers l'intérieur, qui fait saillie dans la cavité annulaire. La paroi de fond de chambre comporte également des languettes 34, 35 faisant saillie à l'intérieur de la cavité annulaire. La paroi de fond de chambre 14 et les languettes 34, 35 portées par celle-ci, à l'intérieur comme à l'extérieur sont tirées d'une même tôle découpée et emboutie comme cela est visible sur la figure 2. On distingue une série de languettes extérieures 34 et une série de languettes intérieures 35. Les languettes extérieures 34 de la paroi de fond de chambre et les languettes 24 de la casquette extérieure sont en nombre égal et se correspondent, chaque languette de la casquette étant appliquée par sa partie saillante contre une languette correspondante de la paroi de fond de chambre. De même, les languettes 25 de la casquette intérieure et les languettes intérieures 35 de la paroi de fond de chambre sont en nombre égal et se correspondent, chaque languette de la casquette intérieure étant appliquée par sa partie saillante contre la languette correspondante de la paroi de fond de chambre. Dans ces positions, les languettes desdites casquettes sont assemblées aux languettes de ladite paroi de fond de chambre. Plus particulièrement, les languettes desdites casquettes et celles de ladite paroi de fond de chambre sont soudées deux à deux et de préférence uniquement à leurs extrémités. Comme mentionné précédemment, la soudure 40 est de préférence du type TIG. En revanche, les parties des languettes 24, 25 solidarisées aux casquettes 16, 17 sont réunies à celles-ci par brasage. Du fait que les languettes sont recourbées de façon à être accolées deux à deux l'une contre l'autre et qu'elles ne sont soudées qu'à leurs extrémités, il est relativement facile de les séparer, par exemple par meulage desdites extrémités soudées. Ces opérations de meulage permettront de démonter les différentes parties de la chambre de combustion pour y effectuer des réparations. Après ces réparations un réassemblage est possible en soudant à nouveau les extrémités des languettes 24, 34 et 25, 35 légèrement raccourcies.More particularly, the caps 16, 17 comprise tongues 24, 25, respectively, projecting inside the annular cavity 20. These tongues are regularly distributed circumferentially. Each cap has as many tabs 24 or 25 as there are injectors but they are offset circumferentially relative to the injectors for better accessibility in case of disassembly. A tongue 24 or 25 has a curved portion 28 conforming to the shape of the inner face of the cap and a portion 29 curved radially inward, which protrudes into the annular cavity. The bottom wall of the chamber also has tabs 34, 35 projecting into the annular cavity. The chamber bottom wall 14 and the tongues 34, 35 carried by it, inside and outside, are drawn from the same cut and stamped sheet as can be seen on FIG. figure 2 . There are a series of outer tongues 34 and a series of inner tongues 35. The outer tongues 34 of the chamber bottom wall and the tongues 24 of the outer cap are equal in number and correspond, each tongue of the cap being applied. by its projecting portion against a corresponding tongue of the chamber bottom wall. Similarly, the tongues 25 of the inner cap and the inner tongues 35 of the bottom wall of the chamber are equal in number and correspond, each tongue of the inner cap being applied by its projecting portion against the corresponding tongue of the wall of the bedroom background. In these positions, the tongues of said caps are assembled to the tongues of said bottom wall of the chamber. More particularly, the tongues of said caps and those of said chamber bottom wall are welded in pairs and preferably only at their ends. As mentioned above, the solder 40 is preferably of the TIG type. On the other hand, the parts of the tongues 24, 25 secured to the caps 16, 17 are joined thereto by brazing. Because the tongues are bent so as to be placed side by side in pairs and welded only at their ends, it is relatively easy to separate them, for example by grinding said welded ends. . These grinding operations will disassemble the various parts of the combustion chamber for repairs. After these repairs reassembly is possible by re-welding the ends of the slightly shortened tabs 24, 34 and 25, 35.

Par ailleurs, la casquette externe 16 et ladite paroi extérieure 12 sont assemblées circonférentiellement par soudage. Comme représenté, la soudure 42 est faite chant contre chant en sorte que l'écoulement de l'air à l'extérieur de la chambre de combustion ne soit pas perturbé. La paroi de fond de chambre 14 n'est pas fixée à ladite pièce extérieure.Furthermore, the outer cap 16 and said outer wall 12 are joined circumferentially by welding. As shown, the weld 42 is edge-to-edge so that the flow of air outside the combustion chamber is not disturbed. The chamber bottom wall 14 is not attached to said outer part.

D'autre part, la paroi intérieure 13 et ladite paroi de fond de chambre 14 sont solidarisées circonférentiellement. Dans le mode de réalisation décrit, les deux parois sont conformées avec des bandes annulaires 43, 44 en contact. Ces bandes peuvent être solidarisées par rivetage ou bouchonnage. Ladite casquette interne 17 comporte également une bande annulaire 47 en contact enveloppant avec la bande annulaire de ladite paroi intérieure. Elle n'est pas fixée à cette paroi intérieure. Cet agencement ne perturbe pratiquement pas l'écoulement d'air à l'intérieur de la veine définie par la paroi intérieure et la casquette interne de la chambre de combustion. Ladite paroi intérieure 13 et la casquette interne 17 ne sont pas solidarisées dans leur zone de contact.On the other hand, the inner wall 13 and said bottom wall chamber 14 are secured circumferentially. In the embodiment described, the two walls are shaped with annular bands 43, 44 in contact. These strips can be secured by riveting or capping. Said inner cap 17 also comprises an annular band 47 in contact enveloping with the annular band of said inner wall. It is not attached to this inner wall. This arrangement does not substantially disturb the flow of air within the vein defined by the inner wall and the inner cap of the combustion chamber. Said inner wall 13 and the inner cap 17 are not secured in their contact zone.

Un assemblage utilisant des viroles aurait, en coupe, une configuration conforme à la figure 3.An assembly using ferrules would, in section, have a configuration in accordance with the figure 3 .

Claims (12)

  1. A jet engine combustion chamber comprising a generally annular outer wall (12), a generally annular inner wall (13), a chamber end wall (14) extending between said outer and inner walls and having injector means mounted thereon, and a fairing co-operating with said chamber end wall to define an annular cavity (20) that houses said injector means, said fairing comprising an annular part referred to as an "outer cap" (16) and an annular part referred to as a "inner cap" (17), wherein said caps include inner fastener parts (24, 25) projecting into said annular cavity, wherein said chamber end wall includes corresponding inner fastener parts (34, 35) projecting into said annular cavity, and wherein the fastener parts of said caps are assembled directly to the fastener parts of said chamber end wall, characterized in that said inner fastener parts are tongues that are distributed circumferentially.
  2. A combustion chamber according to claim 1, characterized in that the tongues (24, 25) of said caps and the tongues (34, 35) of said chamber end wall are welded together.
  3. A combustion chamber according to claim 1 or claim 2, characterized in that both said tongues of said caps, and said tongues of said chamber end wall are curved in such a manner as to extend side by side in pairs one against the other, and in that they are welded together in pairs at their ends (40).
  4. A combustion chamber according to claim 1, characterized in that said inner fastener parts are circumferentially distributed tongues combined to annular rims.
  5. A combustion chamber according to any preceding claim, characterized in that said outer cap (16) and said inner wall (12) are assembled together circumferentially by welding (42).
  6. A combustion chamber according to claim 5, characterized in that said outer cap (16) and said inner wall (12) are butt welded together.
  7. A combustion chamber according to any preceding claim, characterized in that said inner wall (13) and said chamber end wall (14) are united circumferentially.
  8. A combustion chamber according to claim 7, characterized in that said inner wall and said chamber end wall are shaped with contacting annular margins (43, 44) that are untied by riveting or by an interference fit.
  9. A combustion chamber according to any preceding claim, characterized in that said chamber end wall (14) and the tongues (34, 35) carried thereby are portions of a single sheet of metal that has been cut and stamped.
  10. A combustion chamber according to any one of claims 1 to 3, characterized in that the tongues (24, 25) carried by said caps are assembled thereto by brazing.
  11. A combustion chamber according to claim 8, characterized in that said inner cap includes an annular margin (47) in covering contact with said annular margin (43) of said inner wall.
  12. A jet engine characterized by comprising a combustion chamber according to any preceding claim.
EP06112766.8A 2005-04-28 2006-04-19 Easily disassembled combustion chamber with improved aerodynamic performance Active EP1717516B1 (en)

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FR0504283A FR2885201B1 (en) 2005-04-28 2005-04-28 EASILY DISMANTLING COMBUSTION CHAMBER WITH IMPROVED AERODYNAMIC PERFORMANCE

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US (1) US7637111B2 (en)
EP (1) EP1717516B1 (en)
JP (1) JP2006307854A (en)
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FR2911668B1 (en) 2007-01-18 2009-03-20 Snecma Sa COMBUSTION CHAMBER OF A TURBOMACHINE
FR2911669B1 (en) * 2007-01-23 2011-09-16 Snecma FURNITURE FOR COMBUSTION CHAMBER, COMBUSTION CHAMBER WHEN EQUIPPED AND TURBOREACTOR COMPRISING THEM.
FR2920525B1 (en) * 2007-08-31 2014-06-13 Snecma SEPARATOR FOR SUPPLYING THE COOLING AIR OF A TURBINE
FR2964725B1 (en) * 2010-09-14 2012-10-12 Snecma AERODYNAMIC FAIRING FOR BOTTOM OF COMBUSTION CHAMBER
US8938978B2 (en) * 2011-05-03 2015-01-27 General Electric Company Gas turbine engine combustor with lobed, three dimensional contouring
US8938976B2 (en) * 2011-05-20 2015-01-27 Siemens Energy, Inc. Structural frame for gas turbine combustion cap assembly
FR2976346B1 (en) * 2011-06-08 2013-07-05 Turbomeca TURBOMACHINE ANNULAR COMBUSTION CHAMBER
FR2998038B1 (en) * 2012-11-09 2017-12-08 Snecma COMBUSTION CHAMBER FOR A TURBOMACHINE
DE102015213629A1 (en) * 2015-07-20 2017-01-26 Rolls-Royce Deutschland Ltd & Co Kg Cover member and combustion chamber assembly for a gas turbine
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CA2544957A1 (en) 2006-10-28
EP1717516A1 (en) 2006-11-02
FR2885201A1 (en) 2006-11-03
FR2885201B1 (en) 2010-09-17
CN1854610A (en) 2006-11-01
CA2544957C (en) 2014-12-23
JP2006307854A (en) 2006-11-09
RU2006114416A (en) 2007-11-10
US7637111B2 (en) 2009-12-29
RU2411412C2 (en) 2011-02-10
US20060242939A1 (en) 2006-11-02

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