EP1956297A1 - Combustion chamber of a turbomachine - Google Patents

Combustion chamber of a turbomachine Download PDF

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Publication number
EP1956297A1
EP1956297A1 EP08075032A EP08075032A EP1956297A1 EP 1956297 A1 EP1956297 A1 EP 1956297A1 EP 08075032 A EP08075032 A EP 08075032A EP 08075032 A EP08075032 A EP 08075032A EP 1956297 A1 EP1956297 A1 EP 1956297A1
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EP
European Patent Office
Prior art keywords
annular
fairing
combustion chamber
chamber
indentations
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP08075032A
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German (de)
French (fr)
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EP1956297B1 (en
Inventor
Mario César De Sousa
Morgan Robin
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Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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Publication of EP1956297A1 publication Critical patent/EP1956297A1/en
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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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • 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
    • F23R2900/00005—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

Definitions

  • the present invention relates to an annular combustion chamber of a turbomachine, such as an airplane turbojet or turboprop.
  • An annular combustion chamber of a turbomachine comprises two coaxial cylindrical walls, connected at their upstream ends to an annular wall of a very rigid chamber bottom and having at their downstream ends fixing flanges on casings of the turbomachine. It also comprises an upstream annular fairing fixed to the chamber bottom and intended to guide the flow of air entering or bypassing the combustion chamber.
  • the assembly of the upstream part of the combustion chamber is achieved by superposition of the radially inner and outer ends of the fairing on the radially inner and outer ends respectively of the cylindrical walls of the chamber, the assembly being fixed by bolting or welding on radially inner and outer annular flanges respectively of the chamber bottom.
  • Bolting fastening is generally preferred since the maintenance operations performed on the combustion chamber are simpler and less expensive than for welding attachment.
  • the parts of the fairing, the superimposed ends of the cylindrical walls and the chamber bottom have complementary corrugated surfaces, the fasteners being made at the vertices of the corrugations.
  • the present invention relates to a combustion chamber for a turbomachine, which avoids the aforementioned drawbacks of the prior art simply, efficiently and economically.
  • annular combustion chamber of a turbomachine comprising two cylindrical walls radially inner and radially outer respectively relative to the axis of the turbomachine, fixed by bolting at their upstream ends on an inner annular flange and on a outer annular flange of an annular chamber bottom, and an annular fairing extending upstream from the chamber bottom, characterized in that the inner and outer downstream annular ends of the fairing are bolted to the inner annular flanges and outer respectively of the chamber bottom, in axial alignment with the annular ends of the inner and outer walls of the chamber.
  • the assembly of the upstream end of the combustion chamber is thus done by radial superposition of two parts and not more than three parts which reduces the accumulation of stiffness and the accumulation of manufacturing tolerances.
  • the tightening torque to be applied to the bolts can be optimized and the radial deformations of the chamber during the fixing of the fairing and the walls respectively on the bottom wall are reduced.
  • the aligned ends of the fairing and the cylindrical walls of the combustion chamber comprise indentations or complementary corrugations engaged in each other and traversed by fixing bolts on the chamber bottom.
  • the indentations or corrugations of the ends of the fairing and the cylindrical walls comprise an alternation of solid parts and hollow parts, the fastening bolts passing through the solid parts and being distributed in an annular row on the outer annular end of the shroud and on the corresponding end of the outer wall of the chamber, and in an annular row on the inner annular end of the shroud and on the corresponding end of the wall internal of the room.
  • the fixing bolts of the outer annular end of the fairing and the annular end of the outer wall are offset angularly with respect to the fixing bolts of the inner annular end of the fairing and the annular end of the wall. internal.
  • the configuration is such that a fixing bolt of the outer downstream end of the shroud is aligned radially not with a bolt for fixing the inner downstream end of the shroud.
  • each solid part of the indentations or corrugations comprises a single hole for the passage of fixing bolts.
  • the solid portions of the indentations or corrugations of the ends of the fairing comprise the same number of fixing bolts as the solid parts of the indentations or undulations of the ends of the walls of the chamber.
  • the solid portions of the indentations or corrugations of the ends of the fairing comprise a number of fastening bolts different from that of the solid parts of the indentations or corrugations of the ends of the walls of the chamber.
  • the annular fairing can be made in one piece, or in two radially inner and outer annular parts respectively.
  • the invention also relates to a turbomachine, such as an airplane turbojet or turboprop, characterized in that it comprises an annular combustion chamber of the type described above.
  • FIG 1 is a schematic half-view of an annular combustion chamber 10 according to the prior art to the invention, seen in section along the axis of rotation 12 of the turbomachine.
  • the combustion chamber 10 is supplied with air by a diffuser 14 mounted at the outlet of a high-pressure compressor 16. It comprises a radially inner cylindrical wall 18 and a radially outer cylindrical wall 20 connected upstream to an annular chamber bottom 22 and downstream to housings 24 and 26 via an inner annular flange 28 and an outer annular flange 30, respectively.
  • the chamber bottom 22 has openings 36 for the passage of air from the diffuser 14 and the fuel sprayed by injectors 34 carried by the outer casing 26.
  • Each injector 34 comprises a head 38 mounted on the chamber bottom and aligned with the axis 40 of an orifice 36.
  • An annular fairing 60 which extends upstream and which comprises orifices 44 for air passage and passage of the injectors, is fixed on the edges of the chamber bottom 22 with the ends of the cylindrical walls 18 and 20 of the combustion chamber.
  • the assembly of the upstream portion of the combustion chamber is made by interposing the inner ends 46 and outer 48 of the cylindrical walls between, on the one hand, the inner annular ends 50 and outer 52 of the shroud and on the other hand , the inner and outer annular rims 54 and 56 of the chamber bottom. These three pieces thus superimposed are fixed together by bolts 42, which results in a plurality of manufacturing tolerances and a plurality of stiffness.
  • the assembly of the upstream part of the chamber is thus achieved by radial superposition of two pieces and not more than three pieces. Consequently, the impact of the accumulations of the manufacturing tolerances and the respective stiffnesses of the fairing, the walls and the bottom is lower, which facilitates the assembly of the chamber and improves the mechanical strength of the assembly.
  • the tightening torque to be applied to the fairing fastening bolts on the bottom wall flanges can be optimized by taking into account only the fairing and bottom wall stiffness and manufacturing tolerances. Similarly, for fixing the cylindrical walls on the rims of the chamber bottom, only the stiffness and manufacturing tolerances of the walls and the chamber bottom are taken into account. This assembly makes it possible to limit the radial deformations of the fairing and the cylindrical walls and to avoid the formation of additional air leaks that disrupt combustion and air flow.
  • the upstream ends of the inner cylindrical walls 18 and outer 20 comprise corrugations or indentations formed by an alternation of hollow portions 62 and solid portions 48 which extend in alignment with these walls.
  • the inner 50 and outer 52 downstream ends of the fairing comprise corrugations formed by an alternation of hollow portions 64 and solid portions 50.
  • the hollow portions 62 and the solid portions 48 of the cylindrical walls are engaged in the solid portions 50 and the hollow portions 64, respectively, of the annular fairing.
  • the fixing bolts on the chamber bottom pass through the solid portions of the corrugations and are distributed along an outer annular row and an inner annular row.
  • the outer annular row is formed by an alternation of bolts 66 for fixing the outer cylindrical wall on the flange 56 of the chamber bottom and bolts 68 for fixing the outer upstream annular end of the fairing on this flange.
  • the internal annular row of bolts is formed by alternating bolts 70 for fixing the inner cylindrical wall and bolts 72 for fixing the inner upstream annular end of the fairing on the rim 54 of the chamber bottom.
  • the bolts 68 for fixing the outer annular end 52 of the fairing are angularly offset by one pitch relative to the bolts 72 for fixing the inner annular end of the fairing, and the bolts 66 and 72, as well as the bolts 68 and 70 are aligned radially.
  • This method of fixing with angular offset presents the advantage of stiffening the entire combustion chamber, avoiding the formation of deformation lines between an internal bolt 72 and an external bolt 68 which would be diametrically opposed.
  • the frequency levels of the eigen modes of vibration are thus higher which makes it possible to eliminate the risks of propagation of cracks under the effect of the vibrations.
  • each solid part of the indentations or corrugations comprises a single orifice for the passage of a fixing bolt.
  • the solid portions of the corrugations of the ends of the fairing comprise either the same number, for example equal to 2, or a different number of fixing bolts than the solid parts of the corrugations of the ends of the walls of the chamber. .
  • the annular fairing can be made in one piece or in two radially inner and radially outer annular parts.
  • the invention is not limited to the previously described combustion chambers and is generally applicable to all types of combustion chambers, such as, for example, those adapted to receive a plurality of concentric ring nozzle heads. .

Abstract

The chamber (10) has inner and outer cylindrical walls radially arranged with respect to an axis of a turbomachine e.g. turbojet engine, and fixed by bolts at their annular upstream ends (46, 48) on annular inner and outer flanges (54, 56) of an annular chamber bottom. An annular fairing is extended towards the upstream from the bottom. The fairing has outer and inner downstream annular ends (52, 50) fixed by the bolts on the respective flanges, by axially aligning the ends with the ends (46, 48) of the outer and inner walls, where the aligned ends have complementary indentations/corrugations.

Description

La présente invention concerne une chambre annulaire de combustion d'une turbomachine, telle qu'un turboréacteur ou un turbopropulseur d'avion.The present invention relates to an annular combustion chamber of a turbomachine, such as an airplane turbojet or turboprop.

Une chambre annulaire de combustion d'une turbomachine comprend deux parois cylindriques coaxiales, reliées à leurs extrémités amont à une paroi annulaire de fond de chambre très rigide et comportant à leurs extrémités aval des brides de fixation sur des carters de la turbomachine. Elle comprend également un carénage annulaire amont fixé sur le fond de chambre et destiné à orienter le flux d'air en entrée ou en contournement de la chambre de combustion.An annular combustion chamber of a turbomachine comprises two coaxial cylindrical walls, connected at their upstream ends to an annular wall of a very rigid chamber bottom and having at their downstream ends fixing flanges on casings of the turbomachine. It also comprises an upstream annular fairing fixed to the chamber bottom and intended to guide the flow of air entering or bypassing the combustion chamber.

Dans la technique actuelle, l'assemblage de la partie amont de la chambre de combustion est réalisé par superposition des extrémités aval radialement interne et externe du carénage sur les extrémités amont radialement interne et externe respectivement des parois cylindriques de la chambre, l'ensemble étant fixé par boulonnage ou par soudage sur des rebords annulaires radialement interne et externe respectivement du fond de chambre. La fixation par boulonnage est généralement préférée puisque les opérations de maintenance effectuées sur la chambre de combustion sont plus simples et moins coûteuses que pour une fixation par soudage.In the current technique, the assembly of the upstream part of the combustion chamber is achieved by superposition of the radially inner and outer ends of the fairing on the radially inner and outer ends respectively of the cylindrical walls of the chamber, the assembly being fixed by bolting or welding on radially inner and outer annular flanges respectively of the chamber bottom. Bolting fastening is generally preferred since the maintenance operations performed on the combustion chamber are simpler and less expensive than for welding attachment.

L'assemblage de la partie amont de la chambre de combustion par superposition radiale des extrémités du carénage et des parois cylindriques sur les rebords de fond de chambre se traduit par un cumul des tolérances de fabrication lesquelles sont généralement importantes pour des pièces de révolution et par un cumul des raideurs de chacune des pièces. Dès lors, le serrage par un système vis/écrou doit être suffisamment fort pour rattraper ces cumuls de cotes et d'efforts, ce qui peut dépasser la limite acceptable par les vis et/ou entraîner une déformation plastique du carénage et des parois cylindriques principalement, diminuant la tenue mécanique et la durée de vie de la chambre de combustion. La déformation des pièces peut également faire apparaître des ouvertures entre le carénage et les parois créant ainsi des fuites d'air. En outre, lors du fonctionnement de la turbomachine, la chambre est soumise à de fortes vibrations lesquelles peuvent induire un glissement des pièces (carénage, parois et fond de chambre) les unes par rapport aux autres en cas de pertes de fixations.The assembly of the upstream part of the combustion chamber by radial superimposition of the ends of the fairing and the cylindrical walls on the bottom rims of chamber results in an accumulation of manufacturing tolerances which are generally important for parts of revolution and by a combination of the stiffness of each piece. Therefore, the tightening by a screw / nut system must be strong enough to catch these accumulations of dimensions and forces, which may exceed the limit acceptable by the screws and / or cause plastic deformation of the fairing and cylindrical walls mainly. , decreasing the mechanical strength and the service life of the combustion chamber. The deformation of the pieces can also reveal openings between the fairing and the walls thus creating air leaks. In addition, during operation of the turbomachine, the chamber is subjected to strong vibrations which can induce a sliding of the parts (fairing, walls and chamber bottom) relative to each other in case of loss of fixings.

Lorsque le couple de serrage ne permet pas de compenser les raideurs et les jeux de montage des pièces, l'accostage des pièces ne peut être correctement réalisé, ce qui ne permet pas d'obtenir les réactions nécessaires entre les pièces pour faire passer par frottement les efforts qui transitent lors du fonctionnement de la turbomachine. Il en résulte une plus grande facilité de glissement des pièces. Les vibrations de la turbomachine peuvent alors endommager la liaison boulonnée, notamment les vis, ce qui conduit à une augmentation des pertes de fixation et à une destruction des pièces à partir de la liaison.When the tightening torque does not make it possible to compensate for the stiffness and the assembly of the parts, the berthing of the parts can not be correctly realized, which does not make it possible to obtain the necessary reactions between the parts to make pass by friction the forces that pass during the operation of the turbomachine. This results in greater ease of sliding parts. The vibrations of the turbomachine can then damage the bolted connection, including the screws, which leads to an increase in fixing losses and destruction of parts from the connection.

Pour obtenir la souplesse nécessaire à la bonne liaison mécanique des pièces à l'extrémité amont de la chambre de combustion, il a été proposé de réaliser des fentes axiales dans les extrémités du carénage entre les boulons de fixation. Cependant, ces fentes induisent des écoulements d'air supplémentaires autour de la chambre, perturbant l'écoulement d'air et donc le fonctionnement global de la turbomachine. De plus, les extrémités de ces fentes sont sensibles aux vibrations de la turbomachine, ce qui fragilise le carénage.To obtain the flexibility necessary for the good mechanical connection of the parts at the upstream end of the combustion chamber, it has been proposed to make axial slots in the ends of the fairing between the fixing bolts. However, these slots induce additional air flows around the chamber, disrupting the flow of air and therefore the overall operation of the turbomachine. In addition, the ends of these slots are sensitive to the vibrations of the turbomachine, which weakens the fairing.

Dans une autre technique, les parties du carénage, les extrémités superposées des parois cylindriques et du fond de chambre ont des surfaces ondulées complémentaires, les fixations étant réalisées au niveau des sommets des ondulations. Cette solution connue facilite l'accostage des pièces mais crée des déformations au serrage avec un risque de fuites d'air.In another technique, the parts of the fairing, the superimposed ends of the cylindrical walls and the chamber bottom have complementary corrugated surfaces, the fasteners being made at the vertices of the corrugations. This known solution facilitates the docking of parts but creates deformations tightening with a risk of air leakage.

La présente invention a pour objet une chambre de combustion pour turbomachine, qui évite les inconvénients précités de la technique antérieure de façon simple, efficace et économique.The present invention relates to a combustion chamber for a turbomachine, which avoids the aforementioned drawbacks of the prior art simply, efficiently and economically.

Elle propose à cet effet une chambre annulaire de combustion d'une turbomachine, comprenant deux parois cylindriques radialement interne et radialement externe respectivement par rapport à l'axe de la turbomachine, fixées par boulonnage à leurs extrémités amont sur un rebord annulaire interne et sur un rebord annulaire externe d'un fond de chambre annulaire, et un carénage annulaire s'étendant vers l'amont depuis le fond de chambre, caractérisée en ce que les extrémités annulaires aval interne et externe du carénage sont fixées par boulonnage sur les rebords annulaires interne et externe respectivement du fond de chambre, en alignement axiale avec les extrémités annulaires des parois interne et externe de la chambre.It proposes for this purpose an annular combustion chamber of a turbomachine, comprising two cylindrical walls radially inner and radially outer respectively relative to the axis of the turbomachine, fixed by bolting at their upstream ends on an inner annular flange and on a outer annular flange of an annular chamber bottom, and an annular fairing extending upstream from the chamber bottom, characterized in that the inner and outer downstream annular ends of the fairing are bolted to the inner annular flanges and outer respectively of the chamber bottom, in axial alignment with the annular ends of the inner and outer walls of the chamber.

L'assemblage de l'extrémité amont de la chambre de combustion se fait ainsi par superposition radiale de deux pièces et non plus de trois pièces ce qui réduit le cumul des raideurs et le cumul des tolérances de fabrication. Le couple de serrage à appliquer aux boulons peut être optimisé et les déformations radiales de la chambre lors de la fixation du carénage et des parois respectivement sur la paroi de fond sont réduites.The assembly of the upstream end of the combustion chamber is thus done by radial superposition of two parts and not more than three parts which reduces the accumulation of stiffness and the accumulation of manufacturing tolerances. The tightening torque to be applied to the bolts can be optimized and the radial deformations of the chamber during the fixing of the fairing and the walls respectively on the bottom wall are reduced.

Selon une autre caractéristique de l'invention, les extrémités alignées du carénage et des parois cylindriques de la chambre de combustion comportent des indentations ou ondulations complémentaires engagées les unes dans les autres et traversées par des boulons de fixation sur le fond de chambre.According to another characteristic of the invention, the aligned ends of the fairing and the cylindrical walls of the combustion chamber comprise indentations or complementary corrugations engaged in each other and traversed by fixing bolts on the chamber bottom.

Ces indentations ou ondulations confèrent une certaine souplesse radiale au carénage et aux parois cylindriques qui facilite leur fixation sur la paroi de fond. En outre, le risque de glissement des pièces entre elles en cas de rupture de boulons de fixation est fortement diminué par l'utilisation de formes complémentaires entre le carénage et les parois, et par les fixations indépendantes du carénage et des parois sur le fond de chambre.These indentations or corrugations confer a certain radial flexibility to the fairing and the cylindrical walls which facilitates their attachment to the bottom wall. In addition, the risk of sliding parts between them in case of breakage of fixing bolts is greatly reduced by the use of complementary shapes between the fairing and the walls, and by the independent fastenings of the fairing and the walls on the bottom of the frame. bedroom.

Les indentations ou ondulations des extrémités du carénage et des parois cylindriques comprennent une alternance de parties pleines et de parties creuses, les boulons de fixation traversant les parties pleines et étant répartis en une rangée annulaire sur l'extrémité annulaire externe du carénage et sur l'extrémité correspondante de la paroi externe de la chambre, et en une rangée annulaire sur l'extrémité annulaire interne du carénage et sur l'extrémité correspondante de la paroi interne de la chambre.The indentations or corrugations of the ends of the fairing and the cylindrical walls comprise an alternation of solid parts and hollow parts, the fastening bolts passing through the solid parts and being distributed in an annular row on the outer annular end of the shroud and on the corresponding end of the outer wall of the chamber, and in an annular row on the inner annular end of the shroud and on the corresponding end of the wall internal of the room.

La disposition des boulons en une rangée annulaire interne et une rangée annulaire externe permet de diminuer l'encombrement axial.The arrangement of the bolts in an inner annular row and an outer annular row makes it possible to reduce the axial size.

Avantageusement, les boulons de fixation de l'extrémité annulaire externe du carénage et de l'extrémité annulaire de la paroi externe sont décalés angulairement par rapport aux boulons de fixation de l'extrémité annulaire interne du carénage et de l'extrémité annulaire de la paroi interne.Advantageously, the fixing bolts of the outer annular end of the fairing and the annular end of the outer wall are offset angularly with respect to the fixing bolts of the inner annular end of the fairing and the annular end of the wall. internal.

Ainsi la configuration est telle qu'un boulon de fixation de l'extrémité aval externe du carénage n'est aligné pas radialement avec un boulon de fixation de l'extrémité aval interne du carénage. Un tel décalage permet d'éviter la formation de lignes de déformation radiales entre les boulons de fixation internes et externes, ce qui contribue à améliorer la rigidité de la chambre de combustion et à limiter les risques de résonances qui pourraient être à l'origine de la propagation de fissures sous l'effet des vibrations.Thus the configuration is such that a fixing bolt of the outer downstream end of the shroud is aligned radially not with a bolt for fixing the inner downstream end of the shroud. Such an offset makes it possible to avoid the formation of radial deformation lines between the internal and external fixing bolts, which contributes to improving the rigidity of the combustion chamber and to limiting the risks of resonances which could be the cause of the propagation of cracks under the effect of vibrations.

Dans un mode de réalisation de l'invention, chaque partie pleine des indentations ou ondulations comporte un seul orifice de passage de boulons de fixation.In one embodiment of the invention, each solid part of the indentations or corrugations comprises a single hole for the passage of fixing bolts.

Dans un autre mode de réalisation de l'invention, les parties pleines des indentations ou ondulations des extrémités du carénage comprennent le même nombre de boulons de fixation que les parties pleines des indentations ou ondulations des extrémités des parois de la chambre.In another embodiment of the invention, the solid portions of the indentations or corrugations of the ends of the fairing comprise the same number of fixing bolts as the solid parts of the indentations or undulations of the ends of the walls of the chamber.

Dans une variante de réalisation, les parties pleines des indentations ou ondulations des extrémités du carénage comprennent un nombre de boulons de fixation différent de celui des parties pleines des indentations ou ondulations des extrémités des parois de la chambre.In an alternative embodiment, the solid portions of the indentations or corrugations of the ends of the fairing comprise a number of fastening bolts different from that of the solid parts of the indentations or corrugations of the ends of the walls of the chamber.

Le carénage annulaire peut-être réalisé en une seule pièce, ou en deux pièces annulaires radialement interne et externe respectivement.The annular fairing can be made in one piece, or in two radially inner and outer annular parts respectively.

L'invention concerne également une turbomachine, telle qu'un turboréacteur ou un turbopropulseur d'avion, caractérisée en ce qu'elle comprend une chambre annulaire de combustion du type décrit ci-dessus.The invention also relates to a turbomachine, such as an airplane turbojet or turboprop, characterized in that it comprises an annular combustion chamber of the type described above.

D'autres avantages et caractéristiques de l'invention apparaîtront à la lecture de la description suivante faite à titre d'exemple non limitatif et en référence aux dessins annexés dans lesquels :

  • la figure 1 est une demi-vue schématique partielle en coupe axiale d'une chambre de combustion d'un turboréacteur selon la technique antérieure ;
  • la figure 2 est une vue schématique partielle en coupe axiale illustrant l'assemblage de l'extrémité amont de la chambre de combustion selon l'art antérieur ;
  • la figure 3 est une vue schématique partielle en coupe axiale illustrant l'assemblage selon l'invention ;
  • la figure 4 est une vue partielle en perspective d'un mode de réalisation d'une chambre de combustion selon l'invention.
Other advantages and characteristics of the invention will appear on reading the following description given by way of nonlimiting example and with reference to the appended drawings in which:
  • the figure 1 is a partial schematic half-view in axial section of a combustion chamber of a turbojet according to the prior art;
  • the figure 2 is a partial schematic view in axial section illustrating the assembly of the upstream end of the combustion chamber according to the prior art;
  • the figure 3 is a partial schematic view in axial section illustrating the assembly according to the invention;
  • the figure 4 is a partial perspective view of an embodiment of a combustion chamber according to the invention.

On se réfère d'abord à la figure 1 qui est une demi-vue schématique d'une chambre annulaire de combustion 10 selon la technique antérieure à l'invention, vue en coupe selon l'axe de rotation 12 de la turbomachine.We first refer to the figure 1 which is a schematic half-view of an annular combustion chamber 10 according to the prior art to the invention, seen in section along the axis of rotation 12 of the turbomachine.

La chambre de combustion 10 est alimentée en air par un diffuseur 14 monté en sortie d'un compresseur haute pression 16. Elle comprend une paroi cylindrique radialement interne 18 et une paroi cylindrique radialement externe 20 reliées en amont à un fond de chambre annulaire 22 et en aval à des carters 24 et 26 par l'intermédiaire d'une bride annulaire interne 28 et d'une bride annulaire externe 30, respectivement.The combustion chamber 10 is supplied with air by a diffuser 14 mounted at the outlet of a high-pressure compressor 16. It comprises a radially inner cylindrical wall 18 and a radially outer cylindrical wall 20 connected upstream to an annular chamber bottom 22 and downstream to housings 24 and 26 via an inner annular flange 28 and an outer annular flange 30, respectively.

Le fond de chambre 22 comporte des orifices 36 de passage de l'air en provenance du diffuseur 14 et du carburant pulvérisé par des injecteurs 34 portés par le carter externe 26. Chaque injecteur 34 comprend une tête 38 montée sur le fond de chambre et alignée avec l'axe 40 d'un orifice 36. Un carénage annulaire 60 qui s'étend vers l'amont et qui comprend des orifices 44 de passage d'air et de passage des injecteurs, est fixé sur des rebords du fond de chambre 22 avec les extrémités des parois cylindriques 18 et 20 de la chambre de combustion.The chamber bottom 22 has openings 36 for the passage of air from the diffuser 14 and the fuel sprayed by injectors 34 carried by the outer casing 26. Each injector 34 comprises a head 38 mounted on the chamber bottom and aligned with the axis 40 of an orifice 36. An annular fairing 60 which extends upstream and which comprises orifices 44 for air passage and passage of the injectors, is fixed on the edges of the chamber bottom 22 with the ends of the cylindrical walls 18 and 20 of the combustion chamber.

Dans la technique connue représentée en figure 2, l'assemblage de la partie amont de la chambre de combustion est réalisé en intercalant les extrémités interne 46 et externe 48 des parois cylindriques entre, d'une part, les extrémités annulaires interne 50 et externe 52 du carénage et, d'autre part, les rebords annulaire interne 54 et externe 56 du fond de chambre. Ces trois pièces ainsi superposées sont fixées ensemble par des boulons 42, ce qui se traduit par un cumul de tolérances de fabrication et par un cumul de raideurs.In the known art represented in figure 2 , the assembly of the upstream portion of the combustion chamber is made by interposing the inner ends 46 and outer 48 of the cylindrical walls between, on the one hand, the inner annular ends 50 and outer 52 of the shroud and on the other hand , the inner and outer annular rims 54 and 56 of the chamber bottom. These three pieces thus superimposed are fixed together by bolts 42, which results in a plurality of manufacturing tolerances and a plurality of stiffness.

Selon l'invention, ces inconvénients sont évités grâce au fait que comme représenté en figure 3, les extrémités aval interne 50 et externe 52 du carénage sont alignées avec les extrémités annulaires des parois interne 46 et externe 48, respectivement, de la chambre de combustion et sont fixées par boulonnage sur les rebords de la paroi de fond indépendamment des extrémités des parois 46 et 48.According to the invention, these disadvantages are avoided thanks to the fact that as shown in figure 3 , the inner and outer downstream ends 50 and 52 of the fairing are aligned with the annular ends of the inner and outer walls 46 and 48, respectively, of the combustion chamber and are bolted to the flanges of the bottom wall independently of the ends of the walls. 46 and 48.

L'assemblage de la partie amont de la chambre est ainsi réalisé par superposition radiale de deux pièces et non plus de trois pièces. Par conséquent l'impact des cumuls des tolérances de fabrication et des raideurs respectives du carénage, des parois et du fond est plus faible ce qui facilite le montage de la chambre et améliore la tenue mécanique de l'assemblage. Le couple de serrage à appliquer aux boulons de fixation du carénage sur les rebords de la paroi de fond peut être optimisé en tenant compte uniquement des raideurs et des tolérances de fabrication du carénage et de la paroi de fond. De manière similaire, pour la fixation des parois cylindriques sur les rebords du fond de chambre, seules les raideurs et les tolérances de fabrication des parois et du fond de chambre sont prises en compte. Cet assemblage permet de limiter les déformations radiales du carénage et des parois cylindriques et d'éviter la formation de fuites d'air supplémentaires qui perturbent la combustion et l'écoulement d'air.The assembly of the upstream part of the chamber is thus achieved by radial superposition of two pieces and not more than three pieces. Consequently, the impact of the accumulations of the manufacturing tolerances and the respective stiffnesses of the fairing, the walls and the bottom is lower, which facilitates the assembly of the chamber and improves the mechanical strength of the assembly. The tightening torque to be applied to the fairing fastening bolts on the bottom wall flanges can be optimized by taking into account only the fairing and bottom wall stiffness and manufacturing tolerances. Similarly, for fixing the cylindrical walls on the rims of the chamber bottom, only the stiffness and manufacturing tolerances of the walls and the chamber bottom are taken into account. This assembly makes it possible to limit the radial deformations of the fairing and the cylindrical walls and to avoid the formation of additional air leaks that disrupt combustion and air flow.

Dans l'exemple de réalisation représenté aux figures 3 et 4, les extrémités amont des parois cylindriques interne 18 et externe 20 comportent des ondulations ou indentations formées par une alternance de parties creuses 62 et de parties pleines 48 qui s'étendent dans l'alignement de ces parois. De manière similaire, les extrémités aval interne 50 et externe 52 du carénage comprennent des ondulations formées par une alternance de parties creuses 64 et de parties pleines 50. Les parties creuses 62 et les parties pleines 48 des parois cylindriques sont engagées dans les parties pleines 50 et les parties creuses 64, respectivement, du carénage annulaire. Ces ondulations confèrent une souplesse radiale aux parois cylindriques et au carénage facilitant leur fixation sur la paroi de fond. L'utilisation de formes complémentaires aux extrémités du carénage et des parois cylindriques et leur imbrication permet à la chambre de mieux résister aux vibrations de la turbomachine.In the exemplary embodiment shown in Figures 3 and 4 , the upstream ends of the inner cylindrical walls 18 and outer 20 comprise corrugations or indentations formed by an alternation of hollow portions 62 and solid portions 48 which extend in alignment with these walls. Similarly, the inner 50 and outer 52 downstream ends of the fairing comprise corrugations formed by an alternation of hollow portions 64 and solid portions 50. The hollow portions 62 and the solid portions 48 of the cylindrical walls are engaged in the solid portions 50 and the hollow portions 64, respectively, of the annular fairing. These corrugations give radial flexibility to the cylindrical walls and fairing facilitating their attachment to the bottom wall. The use of complementary shapes at the ends of the fairing and cylindrical walls and their nesting allows the chamber to better withstand the vibrations of the turbomachine.

Les boulons de fixation sur le fond de chambre traversent les parties pleines des ondulations et sont répartis suivant une rangée annulaire externe et une rangée annulaire interne. La rangée annulaire externe est formée par une alternance de boulons 66 de fixation de la paroi cylindrique externe sur le rebord 56 du fond de chambre et de boulons 68 de fixation de l'extrémité annulaire amont externe du carénage sur ce rebord. De même, la rangée annulaire interne de boulons est formée par une alternance de boulons 70 de fixation de la paroi cylindrique interne et de boulons 72 de fixation de l'extrémité annulaire amont interne du carénage sur le rebord 54 du fond de chambre.The fixing bolts on the chamber bottom pass through the solid portions of the corrugations and are distributed along an outer annular row and an inner annular row. The outer annular row is formed by an alternation of bolts 66 for fixing the outer cylindrical wall on the flange 56 of the chamber bottom and bolts 68 for fixing the outer upstream annular end of the fairing on this flange. Similarly, the internal annular row of bolts is formed by alternating bolts 70 for fixing the inner cylindrical wall and bolts 72 for fixing the inner upstream annular end of the fairing on the rim 54 of the chamber bottom.

Avantageusement, les boulons 68 de fixation de l'extrémité annulaire externe 52 du carénage sont décalés angulairement d'un pas par rapport aux boulons 72 de fixation de l'extrémité annulaire interne du carénage, et les boulons 66 et 72, ainsi que les boulons 68 et 70, sont alignés radialement. Ce mode de fixation avec décalage angulaire présente l'avantage de rigidifier l'ensemble de la chambre de combustion, en évitant la formation de lignes de déformation entre un boulon interne 72 et un boulon externe 68 qui seraient diamétralement opposés. Les niveaux de fréquences des modes propres de vibration sont ainsi plus élevés ce qui permet d'éliminer les risques de propagation de fissures sous l'effet des vibrations.Advantageously, the bolts 68 for fixing the outer annular end 52 of the fairing are angularly offset by one pitch relative to the bolts 72 for fixing the inner annular end of the fairing, and the bolts 66 and 72, as well as the bolts 68 and 70 are aligned radially. This method of fixing with angular offset presents the advantage of stiffening the entire combustion chamber, avoiding the formation of deformation lines between an internal bolt 72 and an external bolt 68 which would be diametrically opposed. The frequency levels of the eigen modes of vibration are thus higher which makes it possible to eliminate the risks of propagation of cracks under the effect of the vibrations.

Dans la réalisation représentée en figure 3, chaque partie pleine des indentations ou ondulations comporte un seul orifice de passage d'un boulon de fixation.In the embodiment shown in figure 3 each solid part of the indentations or corrugations comprises a single orifice for the passage of a fixing bolt.

Dans des variantes de réalisation non représentées, les parties pleines des ondulations des extrémités du carénage comprennent soit le même nombre, par exemple égal à 2, soit un nombre différent de boulons de fixation que les parties pleines des ondulations des extrémités des parois de la chambre.In alternative embodiments not shown, the solid portions of the corrugations of the ends of the fairing comprise either the same number, for example equal to 2, or a different number of fixing bolts than the solid parts of the corrugations of the ends of the walls of the chamber. .

Le carénage annulaire peut être réalisé en une seule pièce ou bien en deux pièces annulaires radialement interne et radialement externe.The annular fairing can be made in one piece or in two radially inner and radially outer annular parts.

L'invention n'est pas limitée aux chambres de combustion précédemment décrites et est applicable de façon générale à tous les types de chambres de combustion, telles que par exemple celles qui sont adaptées à recevoir une pluralité de têtes d'injecteurs disposées en anneaux concentriques.The invention is not limited to the previously described combustion chambers and is generally applicable to all types of combustion chambers, such as, for example, those adapted to receive a plurality of concentric ring nozzle heads. .

Claims (9)

Chambre annulaire (10) de combustion d'une turbomachine, comprenant deux parois cylindriques radialement interne (18) et radialement externe (20) respectivement par rapport à l'axe de la turbomachine (12), fixées par boulonnage (42) à leurs extrémités amont sur un rebord annulaire interne (54) et sur un rebord annulaire externe (56) d'un fond de chambre annulaire (22), et un carénage annulaire (60) s'étendant vers l'amont depuis le fond de chambre, caractérisée en ce que les extrémités annulaires aval interne (50) et externe (52) du carénage (60) sont fixées par boulonnage sur les rebords annulaires interne (54) et externe (56) respectivement du fond de chambre (22), en alignement axial avec les extrémités annulaires des parois interne (46) et externe (48) de la chambre.An annular combustion chamber (10) of a turbomachine, comprising two radially inner (18) and radially outer (20) cylindrical walls respectively with respect to the axis of the turbomachine (12), bolted (42) at their ends upstream on an inner annular flange (54) and on an outer annular flange (56) of an annular chamber bottom (22), and an annular fairing (60) extending upstream from the chamber bottom, characterized in that the inner (50) and outer (52) annular ends of the shroud (60) are bolted to the inner (54) and outer (56) annular flanges respectively of the chamber bottom (22) in axial alignment. with the annular ends of the inner (46) and outer (48) walls of the chamber. Chambre de combustion selon la revendication 1, caractérisée en ce que les extrémités alignées du carénage et des parois cylindriques de la chambre comportent des indentations ou ondulations complémentaires engagées les unes dans les autres et traversées par des boulons (66, 68, 70, 72) de fixation sur le fond de chambre.Combustion chamber according to claim 1, characterized in that the aligned ends of the fairing and the cylindrical walls of the chamber have complementary indentations or corrugations engaged with one another and traversed by bolts (66, 68, 70, 72). fixing on the chamber bottom. Chambre de combustion selon la revendication 2, caractérisée en ce que les indentations ou ondulations comprennent une alternance de parties pleines et de parties creuses, les boulons de fixation traversant les parties pleines et étant répartis en une rangée annulaire sur l'extrémité annulaire externe (52) du carénage et sur l'extrémité correspondante de la paroi externe (48) de la chambre, et en une rangée annulaire sur l'extrémité annulaire interne (50) du carénage et sur l'extrémité correspondante de la paroi interne (46) de la chambre.Combustion chamber according to claim 2, characterized in that the indentations or corrugations comprise an alternation of solid parts and hollow parts, the fastening bolts passing through the solid parts and being distributed in an annular row on the outer annular end (52). ) of the fairing and on the corresponding end of the outer wall (48) of the chamber, and in an annular row on the inner annular end (50) of the fairing and on the corresponding end of the inner wall (46) of bedroom. Chambre de combustion selon l'une des revendications 1 à 3, caractérisée en ce que les boulons de fixation de l'extrémité annulaire externe (52) du carénage et de l'extrémité annulaire (48) de la paroi externe sont décalés angulairement par rapport aux boulons de fixation de l'extrémité annulaire interne (50) du carénage et de l'extrémité annulaire (46) de la paroi interne.Combustion chamber according to one of claims 1 to 3, characterized in that the fixing bolts of the outer annular end (52) of the shroud and the annular end (48) of the outer wall are offset angularly relative to each other. fixing bolts the inner annular end (50) of the fairing and the annular end (46) of the inner wall. Chambre de combustion selon la revendication 3 ou 4, caractérisée en ce que chaque partie pleine des indentations ou ondulations comporte un seul orifice de passage de boulon de fixation.Combustion chamber according to claim 3 or 4, characterized in that each solid portion of the indentations or corrugations comprises a single fixing bolt passage hole. Chambre de combustion selon la revendication 3 ou 4, caractérisée en ce que les parties pleines des indentations ou ondulations des extrémités du carénage comprennent le même nombre de boulons de fixation que les parties pleines des indentations ou ondulations des extrémités des parois de la chambre.Combustion chamber according to claim 3 or 4, characterized in that the solid parts of the indentations or corrugations of the ends of the fairing comprise the same number of fastening bolts as the solid parts of the indentations or undulations of the ends of the walls of the chamber. Chambre de combustion selon la revendication 3 ou 4, caractérisée en ce que les parties pleines des indentations ou ondulations des extrémités du carénage comprennent un nombre de boulons de fixation différent de celui des parties pleines des indentations ou ondulations des extrémités des parois de la chambre.Combustion chamber according to claim 3 or 4, characterized in that the solid portions of the indentations or corrugations of the ends of the fairing comprise a number of fastening bolts different from that of the solid portions of the indentations or undulations of the ends of the walls of the chamber. Chambre de combustion selon l'une des revendications 1 à 7, caractérisée en ce que le carénage annulaire est réalisé en une seule pièce, ou en deux pièces annulaires radialement interne et externe respectivement.Combustion chamber according to one of claims 1 to 7, characterized in that the annular fairing is formed in one piece, or two radially inner and outer annular parts respectively. Turbomachine, telle qu'un turboréacteur ou un turbopropulseur d'avion, caractérisée en ce qu'elle comprend une chambre annulaire de combustion selon l'une des revendications précédentes.Turbomachine, such as a turbojet or an airplane turboprop, characterized in that it comprises an annular combustion chamber according to one of the preceding claims.
EP08075032.6A 2007-01-18 2008-01-14 Combustion chamber of a turbomachine Active EP1956297B1 (en)

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FR0700325A FR2911668B1 (en) 2007-01-18 2007-01-18 COMBUSTION CHAMBER OF A TURBOMACHINE

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FR2964725B1 (en) * 2010-09-14 2012-10-12 Snecma AERODYNAMIC FAIRING FOR BOTTOM OF COMBUSTION CHAMBER
CN105392700B (en) 2013-07-26 2018-12-18 Mra系统有限责任公司 Aircraft engine hanger
FR3015639B1 (en) * 2013-12-20 2018-08-31 Safran Aircraft Engines COMBUSTION CHAMBER IN A TURBOMACHINE
GB201505502D0 (en) 2015-03-31 2015-05-13 Rolls Royce Plc Combustion equipment
DE102015224990A1 (en) 2015-12-11 2017-06-14 Rolls-Royce Deutschland Ltd & Co Kg Method for assembling a combustion chamber of a gas turbine engine

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EP1717516A1 (en) * 2005-04-28 2006-11-02 Snecma Easily disassembled combustion chamber with improved aerodynamic performance
FR2887015A1 (en) * 2005-06-14 2006-12-15 Snecma Moteurs Sa Combustion chamber for turbomachine, has external and internal axial walls connected to chamber dome having thermal expansion co-efficient different from that of axial wall, where radial gap is provided between nut and ends of axial walls

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GB2252152A (en) * 1991-01-22 1992-07-29 Gen Electric Combustor dome of a gas turbine engine
GB2263733A (en) * 1992-01-28 1993-08-04 Snecma Turbomachine with removable combustion chamber.
EP1431665A2 (en) * 2002-12-20 2004-06-23 General Electric Company Mounting assembly for the forward end of a ceramic matrix composite liner in a gas turbine engine combustor
EP1717516A1 (en) * 2005-04-28 2006-11-02 Snecma Easily disassembled combustion chamber with improved aerodynamic performance
FR2887015A1 (en) * 2005-06-14 2006-12-15 Snecma Moteurs Sa Combustion chamber for turbomachine, has external and internal axial walls connected to chamber dome having thermal expansion co-efficient different from that of axial wall, where radial gap is provided between nut and ends of axial walls

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CA2619422C (en) 2015-11-17
US20090293487A1 (en) 2009-12-03
US8087252B2 (en) 2012-01-03
CA2619422A1 (en) 2008-07-18
FR2911668A1 (en) 2008-07-25
FR2911668B1 (en) 2009-03-20
EP1956297B1 (en) 2016-03-30

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