EP1818614B1 - Annular combustion chamber of a turbomachine with alternating mountings - Google Patents

Annular combustion chamber of a turbomachine with alternating mountings Download PDF

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Publication number
EP1818614B1
EP1818614B1 EP07101652A EP07101652A EP1818614B1 EP 1818614 B1 EP1818614 B1 EP 1818614B1 EP 07101652 A EP07101652 A EP 07101652A EP 07101652 A EP07101652 A EP 07101652A EP 1818614 B1 EP1818614 B1 EP 1818614B1
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EP
European Patent Office
Prior art keywords
chamber
combustion chamber
longitudinal walls
chamber bottom
fixings
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EP07101652A
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German (de)
French (fr)
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EP1818614A1 (en
Inventor
Florian Bessagnet
Mario De Sousa
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Safran Aircraft Engines SAS
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SNECMA SAS
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—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
    • F23R3/02—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
    • F23R3/42—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
    • F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00017—Assembling combustion chamber liners or subparts

Description

Arrière-plan de l'inventionBackground of the invention

La présente invention se rapporte au domaine général des chambres de combustion annulaires pour turbomachine munies d'un carénage monobloc de protection des systèmes d'injection de carburant.The present invention relates to the general field of turbomachine annular combustion chambers provided with a one-piece fairing protection of fuel injection systems.

Une chambre de combustion annulaire de turbomachine est généralement formée de deux parois longitudinales de révolution (une paroi externe et une paroi interne) qui sont reliées en amont par une paroi transversale formant fond de chambre.An annular turbomachine combustion chamber is generally formed of two longitudinal walls of revolution (an outer wall and an inner wall) which are connected upstream by a transverse wall forming a chamber bottom.

La présente invention vise plus particulièrement les chambres de combustion qui comportent également un carénage monobloc monté en amont du fond de chambre. Le carénage permet notamment de protéger les systèmes d'injection de carburant qui sont montés sur le fond de chambre.The present invention relates more particularly to combustion chambers which also comprise a monobloc fairing mounted upstream of the chamber bottom. The fairing allows in particular to protect the fuel injection systems that are mounted on the chamber floor.

L'assemblage de ces différents éléments de la chambre de combustion s'effectue au moyen de boulonnages montés au niveau des parois interne et externe. De façon plus précise, le fond de chambre et le carénage comportent chacun une bride interne et une bride externe sur lesquelles sont fixées par boulonnage respectivement la paroi interne et la paroi externe de la chambre de combustion, ces parois longitudinales étant intercalées entre le carénage et le fond de chambre. Ainsi, un même boulonnage traverse à la fois l'une des parois longitudinales, le fond de chambre et le carénage de la chambre de combustion. On pourra se référer par exemple au document GB-A-2 263 733 .The assembly of these different elements of the combustion chamber is performed by means of bolting mounted at the inner and outer walls. More specifically, the chamber base and the fairing each comprise an internal flange and an external flange on which are fixed by bolting respectively the inner wall and the outer wall of the combustion chamber, these longitudinal walls being interposed between the fairing and the bedroom floor. Thus, the same bolting through both one of the longitudinal walls, the chamber bottom and the fairing of the combustion chamber. We can refer for example to the document GB-A-2,263,733 .

En pratique, ce type d'architecture de chambre de combustion pose de nombreux problèmes. Notamment, les différents éléments de la chambre de combustion ont des tolérances de fabrication importantes, ce qui conduit à un empilage des tolérances ayant pour conséquence un mauvais accostage entre ces éléments lors du montage de la chambre de combustion, ce qui engendre une perte au niveau du serrage transitant entre les brides. En effet, la part du serrage qui est utilisée pour déformer la chambre est soustraite de l'effort de réactions entre ses composants. Lorsque cet effort de réaction diminue, l'effort nécessaire pour faire glisser les pièces entre elles est donc moindre. Un couple de serrage supplémentaire est donc nécessaire pour rattraper les jeux provenant des tolérances de fabrication des composants et ainsi garder le bon effort de serrage pour le passage des efforts de glissement transitant dans la liaison. De ce fait, en fonctionnement, les vibrations causées par la combustion des gaz à l'intérieur de la chambre de combustion entraînent la formation de criques au niveau des boulonnages sur le carénage et/ou le fond de chambre. De telles criques sont particulièrement préjudiciables à la durée de vie de la chambre de combustion.In practice, this type of combustion chamber architecture poses many problems. In particular, the various elements of the combustion chamber have significant manufacturing tolerances, which leads to a stack of tolerances resulting in poor docking between these elements during assembly of the combustion chamber, which causes a loss in clamping passing between the flanges. Indeed, the part of the clamping which is used to deform the chamber is subtracted from the reaction force between its components. When this reaction force decreases, the effort required to slide the pieces together is therefore less. An extra tightening torque is therefore necessary to make up for the games coming from manufacturing tolerances of the components and thus keep the proper tightening force for the passage of sliding forces passing through the connection. Therefore, in operation, the vibrations caused by the combustion of the gases inside the combustion chamber cause the formation of cracks in the bolting on the shroud and / or the chamber bottom. Such cracks are particularly detrimental to the life of the combustion chamber.

Objet et résumé de l'inventionObject and summary of the invention

La présente invention a donc pour but principal de pallier de tels inconvénients en proposant une architecture de chambre de combustion annulaire de montage facilité et ayant une souplesse suffisante pour éviter la formation de criques tout en gardant une efficacité de serrage utile.The main object of the present invention is therefore to overcome such disadvantages by proposing an annular combustion chamber architecture which is easy to mount and has sufficient flexibility to prevent the formation of cracks while maintaining a useful clamping efficiency.

A cet effet, il est prévu une chambre de combustion annulaire de turbomachine formée de parois longitudinales interne et externe reliées en amont par un fond de chambre transversal et comportant un carénage monobloc couvrant ledit fond de chambre, les parois longitudinales étant chacune insérée entre des brides correspondantes du fond de chambre et du carénage, caractérisée en ce que les parois longitudinales, le fond de chambre et le carénage sont assemblés entre eux par l'intermédiaire d'une pluralité de premières fixations uniquement entre les parois longitudinales et le fond de chambre alternant avec une pluralité de secondes fixations distinctes des premières fixations uniquement entre les parois longitudinales et le carénage.For this purpose, there is provided an annular turbomachine combustion chamber formed of internal and external longitudinal walls connected upstream by a transverse chamber bottom and comprising a one-piece fairing covering said chamber bottom, the longitudinal walls being each inserted between flanges. corresponding components of the chamber bottom and the fairing, characterized in that the longitudinal walls, the chamber base and the fairing are assembled together by means of a plurality of first fasteners only between the longitudinal walls and the alternating chamber bottom with a plurality of second distinct fastenings of the first fasteners only between the longitudinal walls and the fairing.

Alterner la fixation des parois longitudinales sur le fond de chambre et le carénage de la chambre de combustion permet de réduire l'empilage des tolérances de fabrication de ces éléments d'un tiers. Il en résulte une rigidité moindre de l'assemblage et ainsi un meilleur accostage entre ces éléments lors du montage de la chambre et une réduction des risques de formation de criques.Alternating the fixing of the longitudinal walls on the chamber bottom and the fairing of the combustion chamber makes it possible to reduce the stacking of manufacturing tolerances of these elements by one third. This results in less rigidity of the assembly and thus a better docking between these elements during assembly of the chamber and a reduction of the risk of formation of cracks.

Par ailleurs, une solution consistant simplement à réduire les tolérances de fabrication des éléments de la chambre de combustion s'avèrerait beaucoup plus coûteuse à réaliser que la mise en oeuvre de la présente invention.Moreover, a solution consisting simply of reducing the manufacturing tolerances of the elements of the combustion chamber would be much more expensive to achieve than the implementation of the present invention.

Selon une disposition avantageuse de l'invention, il est prévu Autant de premières fixations entre les parois longitudinales et le fond de chambre que de secondes fixations entre les parois longitudinales et le carénage.According to an advantageous arrangement of the invention, there are provided as many first fastenings between the longitudinal walls and the bottom of chamber that seconds fastenings between the longitudinal walls and the fairing.

Selon une autre disposition avantageuse de l'invention, les premières fixations entre la paroi longitudinale interne et le fond de chambre sont situées en vis-à-vis des secondes fixations entre la paroi longitudinale externe et le carénage, et les secondes fixations entre la paroi longitudinale interne et le carénage sont situées en vis-à-vis des premières fixations entre la paroi longitudinale externe et le fond de chambre. Cette disposition permet d'éviter toute dissymétrie cyclique des souplesses et rigidités azimutales et donc de prévenir tout phénomène d'endommagement que peuvent générer les sollicitations vibratoires de la chambre de combustion lors de son fonctionnement.According to another advantageous arrangement of the invention, the first fasteners between the inner longitudinal wall and the chamber bottom are located vis-à-vis the second fastenings between the outer longitudinal wall and the fairing, and the second fastenings between the wall internal longitudinal and the fairing are located vis-à-vis the first fasteners between the outer longitudinal wall and the chamber bottom. This arrangement makes it possible to avoid any cyclic dissymmetry of the azimuthal flexibilities and rigidities and thus to prevent any phenomenon of damage that can be generated by the vibratory stresses of the combustion chamber during its operation.

Les brides du fond de chambre comportent de préférence des encoches pratiquées au niveau des secondes fixations entre les parois longitudinales et le carénage. De même, les brides du carénage comportent avantageusement des encoches pratiquées au niveau des premières fixations entre les parois longitudinales et le fond de chambre. La présence d'encoches permet ainsi de faciliter l'assemblage de la chambre de combustion.The flanges of the chamber bottom preferably comprise notches made at the second fastenings between the longitudinal walls and the shroud. Similarly, the flanges of the fairing advantageously comprise notches made at the first fasteners between the longitudinal walls and the bottom chamber. The presence of notches thus facilitates the assembly of the combustion chamber.

La présente invention a également pour objet une turbomachine ayant une chambre de combustion annulaire telle que définie précédemment.The present invention also relates to a turbomachine having an annular combustion chamber as defined above.

Brève description des dessinsBrief description of the drawings

D'autres caractéristiques et avantages de la présente invention ressortiront de la description faite ci-dessous, en référence aux dessins annexés qui en illustrent un exemple de réalisation dépourvu de tout caractère limitatif. Sur les figures :

  • la figure 1 est une vue en coupe longitudinale d'une chambre de combustion de turbomachine selon l'invention ;
  • la figure 2 est une vue partielle et en perspective de la chambre de combustion de la figure 1 avant son assemblage ;
  • la figure 3 est une vue partielle et en perspective de la chambre de combustion de la figure 2 après son assemblage ; et
  • la figure 4 est une vue schématique de la chambre de combustion de la figure 1 montrant l'emplacement des différentes fixations entre les éléments la constituant.
Other features and advantages of the present invention will emerge from the description given below, with reference to the accompanying drawings which illustrate an embodiment having no limiting character. In the figures:
  • the figure 1 is a longitudinal sectional view of a turbomachine combustion chamber according to the invention;
  • the figure 2 is a partial view in perspective of the combustion chamber of the figure 1 before assembly;
  • the figure 3 is a partial view in perspective of the combustion chamber of the figure 2 after assembly; and
  • the figure 4 is a schematic view of the combustion chamber of the figure 1 showing the location of the various fasteners between the constituent elements.

Description détaillée d'un mode de réalisationDetailed description of an embodiment

Les figures 1 à 4 illustrent une chambre de combustion pour turbomachine selon l'invention.The Figures 1 to 4 illustrate a combustion chamber for a turbomachine according to the invention.

Une telle turbomachine, par exemple aéronautique, comporte notamment une section de compression (non représentée) dans laquelle de l'air est comprimé avant d'être injecté dans un carter de chambre 2, puis dans une chambre de combustion 4 montée à l'intérieur de celui-ci.Such a turbomachine, for example aeronautical, comprises in particular a compression section (not shown) in which air is compressed before being injected into a chamber housing 2, then into a combustion chamber 4 mounted inside. of it.

L'air comprimé est introduit dans la chambre de combustion et mélangé à du carburant avant d'y être brûlé. Les gaz issus de cette combustion sont alors dirigés vers une turbine haute-pression 5 disposée en sortie de la chambre de combustion.Compressed air is introduced into the combustion chamber and mixed with fuel before being burned. The gases resulting from this combustion are then directed to a high-pressure turbine 5 disposed at the outlet of the combustion chamber.

La chambre de combustion 4 est de type annulaire. Elle est formée d'une paroi annulaire interne 6 et d'une paroi annulaire externe 8 qui sont réunies en amont (par rapport au sens d'écoulement des gaz de combustion dans la chambre de combustion) par une paroi annulaire transversale 10 formant fond de chambre.The combustion chamber 4 is of annular type. It is formed of an inner annular wall 6 and an outer annular wall 8 which are connected upstream (with respect to the direction of flow of the combustion gases in the combustion chamber) by a transverse annular wall 10 forming a bottom wall. bedroom.

La chambre de combustion comporte également un carénage annulaire et monobloc 12 (c'est-à-dire réalisé en une seule et même pièce) couvrant le fond de chambre 10.The combustion chamber also comprises an annular and monoblock fairing 12 (that is to say made in one and the same piece) covering the chamber bottom 10.

Les parois longitudinales 6, 8 de la chambre de combustion s'étendent selon un axe longitudinal X-X qui peut être légèrement incliné par rapport à l'axe longitudinal Y-Y de la turbomachine comme représenté sur la figure 1.The longitudinal walls 6, 8 of the combustion chamber extend along a longitudinal axis XX which may be slightly inclined with respect to the longitudinal axis YY of the turbomachine as shown in FIG. figure 1 .

Bien entendu, la présente invention s'applique également aux chambres de combustion dont les parois longitudinales ne sont pas inclinées par rapport à l'axe longitudinal de la turbomachine.Of course, the present invention also applies to combustion chambers whose longitudinal walls are not inclined relative to the longitudinal axis of the turbomachine.

Par ailleurs, le fond de chambre 10 et le carénage 12 de la chambre de combustion sont chacun pourvus d'une pluralité d'ouvertures, respectivement 14 et 16, pour le passage de systèmes d'injection de carburant 18.Furthermore, the bottom chamber 10 and the fairing 12 of the combustion chamber are each provided with a plurality of openings, respectively 14 and 16, for the passage of fuel injection systems 18.

Les composants principaux de la chambre de combustion (à savoir ; les parois longitudinales 6, 8, le fond de chambre 10 et le carénage 12) sont assemblés entre eux à l'aide d'une pluralité de systèmes de fixation 20 régulièrement répartis sur toute la circonférence de la chambre de combustion et formés chacun d'une vis 20a et d'un écrou de serrage 20b.The main components of the combustion chamber (i.e. the longitudinal walls 6, 8, the chamber bottom 10 and the fairing 12) are assembled together by means of a plurality of fixing systems 20 regularly distributed over the entire circumference of the combustion chamber and each formed of a screw 20a and a clamping nut 20b.

De façon plus précise, comme représenté sur les figures 2 et 3, le fond de chambre 10 comporte une bride interne 22 et une bride externe 24 s'étendant longitudinalement vers l'amont et munie chacune de trous, respectivement 22a et 24a, pour le passage de vis de fixation 20a.More specifically, as shown on the figures 2 and 3 , the chamber bottom 10 has an internal flange 22 and an external flange 24 extending longitudinally upstream and each provided with holes, 22a and 24a respectively, for the passage of fastening screws 20a.

De même, le carénage monobloc 12 comprend une bride interne 26 et une bride externe 28 qui s'étendent longitudinalement vers l'aval et qui sont chacune munie de trous, respectivement 26a et 28a, pour le passage des vis de fixation 20a.Similarly, the one-piece fairing 12 comprises an inner flange 26 and an outer flange 28 which extend longitudinally downstream and which are each provided with holes, respectively 26a and 28a, for the passage of the fastening screws 20a.

Quant aux parois longitudinales 6, 8 de la chambre de combustion, elles sont également percées à leur extrémité amont d'une pluralité de trous, respectivement 6a et 8a, pour le passage des vis de fixation 20a.As for the longitudinal walls 6, 8 of the combustion chamber, they are also drilled at their upstream end of a plurality of holes, respectively 6a and 8a, for the passage of the fixing screws 20a.

L'assemblage de ces composants de la chambre de combustion s'effectue en intercalant les parois longitudinales 6, 8 entre les brides respectives du fond de chambre 10 et du carénage 12 comme représenté sur les figures 1 et 3. L'ensemble est alors maintenu par les vis de fixation 20a sur lesquelles sont serrées les écrous 20b.The assembly of these components of the combustion chamber is performed by interposing the longitudinal walls 6, 8 between the respective flanges of the chamber bottom 10 and the fairing 12 as shown in the drawings. figures 1 and 3 . The assembly is then held by the fixing screws 20a on which are tightened the nuts 20b.

Selon l'invention, les parois longitudinales 6, 8, le fond de chambre 10 et le carénage 12 sont assemblés alternativement deux par deux par les systèmes de fixation 20.According to the invention, the longitudinal walls 6, 8, the chamber bottom 10 and the shroud 12 are assembled alternately two by two by the fastening systems 20.

En d'autres termes, comme représenté par la figure 4, les systèmes de fixation 20 pour l'assemblage de ces éléments se répartissent en deux groupes : un premier groupe de systèmes de fixation 20' venant serrer uniquement les parois longitudinales 6, 8 et les brides correspondantes 22, 24 du fond de chambre 10, et un second groupe de systèmes de fixation 20" venant serrer uniquement les parois longitudinales 6, 8 et les brides correspondantes 26, 28 du carénage 12, les systèmes de fixation 20" du second groupe étant distincts des systèmes de fixation 20' du premier groupe et disposés en alternance avec ceux-ci.In other words, as represented by the figure 4 , the fastening systems 20 for assembling these elements are divided into two groups: a first group of fastening systems 20 'which clamp only the longitudinal walls 6, 8 and the corresponding flanges 22, 24 of the chamber bottom 10, and a second group of fastening systems 20 "which grip only the longitudinal walls 6, 8 and the corresponding flanges 26, 28 of the shroud 12, the fastening systems 20" of the second group being distinct from the fastening systems 20 'of the first group and arranged alternately therewith.

Ainsi, chacun des systèmes de fixation 20', 20" appartenant à ces groupes ne traverse que deux des éléments constituant la chambre de combustion, à savoir soit l'une des parois longitudinales 6, 8 et la bride 22, 24 correspondante du fond de chambre 10, soit l'une des longitudinales 6, 8 et la bride 26, 28 correspondante du carénage 12.Thus, each of the fastening systems 20 ', 20 "belonging to these groups passes through only two of the elements constituting the chamber of combustion, namely either one of the longitudinal walls 6, 8 and the corresponding flange 22, 24 of the chamber bottom 10, or one of the longitudinal 6, 8 and the corresponding flange 26, 28 of the shroud 12.

Selon une caractéristique avantageuse de l'invention illustrée sur la figure 4, il est prévu autant de systèmes de fixation 20' appartenant au premier groupe (c'est-à-dire de systèmes de fixation entre les parois longitudinales 6, 8 et le fond de chambre 10) que de systèmes de fixation 20" appartenant au second groupe (c'est-à-dire de systèmes de fixations entre les parois longitudinales 6, 8 et le carénage 12). Par exemple, il peut être prévu huit systèmes de fixation pour chaque groupe.According to an advantageous characteristic of the invention illustrated on the figure 4 , there are provided as many fastening systems 20 'belonging to the first group (that is to say fastening systems between the longitudinal walls 6, 8 and the chamber bottom 10) that fastening systems 20 "belonging to the second group (i.e. fastening systems between the longitudinal walls 6, 8 and the shroud 12.) For example, eight fastening systems can be provided for each group.

Par ailleurs, on notera que pour obtenir une alternance de systèmes de fixation 20', 20" appartenant à chaque groupe qui soit uniforme sur toute la circonférence de la chambre de combustion, il est nécessaire d'avoir un nombre pair de systèmes de fixation.Furthermore, it will be noted that in order to obtain an alternation of fixing systems 20 ', 20 "belonging to each group which is uniform over the entire circumference of the combustion chamber, it is necessary to have an even number of fixing systems.

Selon une autre caractéristique avantageuse de l'invention également illustrée sur la figure 4, les systèmes de fixations 20' entre la paroi longitudinale interne 6 et le fond de chambre 10 sont situées en vis-à-vis des systèmes de fixations 20" entre la paroi longitudinale externe 8 et le carénage 12, et les systèmes de fixations 20" entre la paroi longitudinale interne 6 et le carénage 12 sont situées en vis-à-vis des systèmes de fixations 20' entre la paroi longitudinale externe 8 et le fond de chambre 10.According to another advantageous characteristic of the invention also illustrated on the figure 4 the fastening systems 20 'between the inner longitudinal wall 6 and the chamber bottom 10 are located opposite the fastening systems 20 "between the outer longitudinal wall 8 and the shroud 12, and the fastening systems 20 "between the inner longitudinal wall 6 and the fairing 12 are located vis-à-vis the fastening systems 20 'between the outer longitudinal wall 8 and the chamber bottom 10.

Par l'expression « situés en vis-à-vis », on entend que les systèmes de fixation sont alignés selon une même direction radiale définie par rapport à l'axe longitudinal Y-Y de la turbomachine comme illustré sur la figure 4.The expression "located opposite" means that the fastening systems are aligned in the same radial direction defined with respect to the longitudinal axis YY of the turbomachine as shown in FIG. figure 4 .

Selon encore une autre caractéristique avantageuse de l'invention, la bride interne 22 et la bride externe 24 du fond de chambre 10 comportent des encoches, respectivement 30 et 32, qui sont pratiquées au niveau des systèmes de fixation 20" entre les parois longitudinales 6, 8 et le carénage 12.According to yet another advantageous characteristic of the invention, the inner flange 22 and the outer flange 24 of the chamber bottom 10 comprise notches, respectively 30 and 32, which are formed at the level of the fastening systems 20 "between the longitudinal walls 6 , 8 and the fairing 12.

De même, la bride interne 26 et la bride externe 28 du carénage 12 comportent de préférence des encoches, respectivement 34 et 36, qui sont pratiquées au niveau des systèmes de fixation 20' entre les parois longitudinales 6, 8 et le fond de chambre 10.Similarly, the inner flange 26 and the outer flange 28 of the shroud 12 preferably have notches, respectively 34 and 36, which are formed at the fastening systems 20 'between the longitudinal walls 6, 8 and the chamber bottom 10 .

La présence de telles encoches 30 à 36 sur les brides du fond de chambre et du carénage a pour avantage de faciliter l'assemblage de ces deux éléments de la chambre de combustion. Bien entendu, de telles encoches sont de dimensions suffisantes pour permettre le passage des vis 20a et des écrous 20b des systèmes de fixation.The presence of such notches 30 to 36 on the flanges of the chamber bottom and fairing has the advantage of facilitating the assembly of these two elements of the combustion chamber. Of course, such slots are of sufficient size to allow the passage of the screws 20a and nuts 20b of the fastening systems.

Claims (6)

  1. Turbine engine annular combustion chamber made up of inner (6) and outer (8) longitudinal walls connected upstream by a transverse chamber bottom (10) and comprising a single-piece cowling (12) covering said chamber bottom, the longitudinal walls (6, 8) each being inserted between corresponding flanges (22, 24; 26, 28) of the chamber bottom (10) and of the cowling (12), characterised in that the longitudinal walls (6, 8), the chamber bottom (10) and the cowling (12) are assembled together by means of a plurality of first fixings (20') only between the longitudinal walls (6, 8) and the chamber bottom (10) alternating with a plurality of second fixings (20") distinct from the first fixings (20') only between the longitudinal walls (6, 8) and the cowling (12).
  2. Chamber according to Claim 1, comprising as many first fixings (20') between the longitudinal walls (6, 8) and the chamber bottom (10) as second fixings (20") between the longitudinal walls and the cowling (12).
  3. Chamber according to one of Claims 1 and 2, wherein the first fixings (20') between the inner longitudinal wall (6) and the chamber bottom (10) are situated opposite the second fixings (20") between the outer longitudinal wall (8) and the cowling (12), and the second fixings (20") between the inner longitudinal wall (6) and the cowling (12) are situated opposite the first fixings (20') between the outer longitudinal wall (8) and the chamber bottom (10).
  4. Chamber according to any one of Claims 1 to 3, wherein the flanges (22, 24) of the chamber bottom (10) comprise notches (30, 32) made in the region of the second fixings (20") between the longitudinal walls (6, 8) and the cowling (12).
  5. Chamber according to any one of Claims 1 to 4, wherein the flanged (26, 28) of the cowling (12) comprise notches (34, 36) made in the region of the first fixings (20') between the longitudinal walls (6, 8) and the chamber bottom (10).
  6. Turbine engine, characterised in that it comprises an annular combustion chamber (4) according to any one of Claims 1 to 5.
EP07101652A 2006-02-08 2007-02-02 Annular combustion chamber of a turbomachine with alternating mountings Active EP1818614B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0650446A FR2897145B1 (en) 2006-02-08 2006-02-08 ANNULAR COMBUSTION CHAMBER FOR TURBOMACHINE WITH ALTERNATE FIXINGS.

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Publication number Publication date
FR2897145B1 (en) 2013-01-18
RU2007104730A (en) 2008-08-20
CN101016998A (en) 2007-08-15
FR2897145A1 (en) 2007-08-10
RU2421663C2 (en) 2011-06-20
CA2577523A1 (en) 2007-08-08
US7757495B2 (en) 2010-07-20
EP1818614A1 (en) 2007-08-15
US20070180809A1 (en) 2007-08-09
CA2577523C (en) 2014-09-30

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