EP3899371B1 - Turbomachine combustion chamber - Google Patents

Turbomachine combustion chamber Download PDF

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Publication number
EP3899371B1
EP3899371B1 EP19845596.6A EP19845596A EP3899371B1 EP 3899371 B1 EP3899371 B1 EP 3899371B1 EP 19845596 A EP19845596 A EP 19845596A EP 3899371 B1 EP3899371 B1 EP 3899371B1
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EP
European Patent Office
Prior art keywords
wall
injector
combustion chamber
passage
connection
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EP19845596.6A
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German (de)
French (fr)
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EP3899371C0 (en
EP3899371A1 (en
Inventor
Damien FAUVET
Marc NGUYEN
Baptiste Guerin
Jean-Michel Guimbard
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Turbotech
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Turbotech
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
    • F23R3/48—Flame tube interconnectors, e.g. cross-over tubes
    • 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
    • F23R3/002—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
    • F23R3/005—Combined with pressure or heat exchangers
    • 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
    • F23R3/54—Reverse-flow combustion chambers
    • 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
    • F23R2900/00001—Arrangements using bellows, e.g. to adjust volumes or reduce thermal stresses

Definitions

  • the present invention relates to the field of regenerative cycle turbines intended in particular for the production of on-board electrical or mechanical energy from fuels for aeronautical, land, maritime vehicles and light mobile units.
  • the exhaust gases exit the turbine at high temperatures (above 500°C), while the temperature of the air leaving the compressor is lower (typically between 200°C and 400°C). °C), with circulation through a heat exchanger inserted between the exhaust gases and the compressed air allowing the air to be partially heated before entering the combustion chamber, which reduces fuel consumption.
  • the invention relates more particularly to the combustion chamber and the injection of fuel into the combustion chamber.
  • German patent DE1254911 providing hook-shaped injection nozzles mounted in the injection nozzle body, which is fixed in the flame holder with its nozzle tip, so as to be movable relative to the walls of the combustion chamber.
  • the exterior part of the hook-shaped injection nozzle body is slidably mounted in a guide, possibly associated with the exterior wall of the combustion chamber, and a clamping device directed parallel to the tip mouthpiece of the nozzle is designed to hold the front end of the mouthpiece against a stop fixed in a hub of the flame holder.
  • the problem posed by the solutions of the prior art concerns turbines having a combustion chamber isolated from the outside by a double wall, two walls defining an annular conduit for the circulation of a flow of compressed air coming from the compressor and the third wall being the exterior wall of the combustion chamber, allowing the circulation of the same flow of air heated before passing through a heat exchanger.
  • the injector(s) must pass through the three walls in a sealed manner or at the very least with a controlled leak. This results in a hyperstatic assembly which does not make it possible to absorb the longitudinal thermal expansions of the injector, nor the radial and longitudinal thermal expansions of the metal walls subjected to strongly differentiated temperatures.
  • the injector passes through the walls of the combustion chamber through simple holes, referenced 38, 48 and 52.
  • This document of the prior art proposes to position the injector coaxially inside each of the coaxial holes 52, 48 and 38 provided in the housing 50.
  • This solution therefore leads to multiple disadvantages: on the one hand, the radial expansion of the injector is different from the surface expansion of the walls, which leads either to leaks between the periphery of the injector and the edge of the passage holes in the wall, or to tightness of the edges of the holes around the wall of the injector, which limits the possibilities of radial movement and can lead to deformation and fatigue of the walls .
  • the present invention relates to a combustion chamber of a turbomachine according to the subject of claim 1.
  • FIG. 1 describes a configuration not forming part of the invention as defined by the claims and represents a perspective view of the turbomachine, comprising an exchanger (1), a compressor (2), a combustion chamber (3) and a turbine (4).
  • a conical deflector (11) coaxial with the exchanger (1) circulates the hot gases coming from the turbine (4) towards an evacuation outlet (12) after passing through the exchanger (2), crossing two cassettes (5, 6) between the tubes.
  • the exchanger (2) consists of a tube exchanger, comprising two coaxial annular cassettes (5, 6).
  • the outer cassette (5) is made up of an assembly of parallel tubes, made of a metal alloy resistant to high temperatures, for example refractory stainless steel 347.
  • this exterior cassette (5) is made up of 2000 tubes with a length of 300 millimeters, an interior section of 2.8 millimeters and an exterior section of 3 millimeters.
  • the tubes are held in a known manner by spacers to define passages for hot gases coming from the turbine.
  • the tubes form a sleeve with an outer radius of 158 millimeters and an inner radius of 128 millimeters.
  • the inner cassette (6) is made up of 2000 tubes with a length of 300 millimeters, an inner section of 2.8 millimeters and an outer section of 3 millimeters.
  • the tubes form a sleeve with an outer radius of 123 millimeters and an inner radius of 67 millimeters.
  • the two cassettes (5, 6) are coaxial and embedded one inside the other.
  • Each of the cassettes (5, 6) comprises, at each end, a front sealing plate pierced for the passage of the tubes, and ensuring the constant center distance of the tubes.
  • the tubes are brazed or welded to ensure tightness at their connection with the front plates.
  • This closing structure (8) is made up of two coaxial interlocking parts, having the general shape of a rum baba mold, in refractory stainless steel 347 with a thickness of 2 millimeters.
  • the outer part (9) has an outer section corresponding to the outer section of the outer cassette (5) and an inner section corresponding to the inner section of the inner cassette (6).
  • the inner part (10) has an outer section corresponding to the inner section of the outer cassette (5) and an inner section corresponding to the outer section of the inner cassette (6).
  • Each of the parts (9, 10) has a symmetry of revolution along the axis of the turbomachine, with a constant longitudinal section.
  • the closing structure (8) ensures the deflection of gases coming from the outer cassette (5) towards the tubes constituting the inner cassette (6).
  • This solution ensures a double passage of gases in the exchanger (1), which significantly increases its thermal efficiency for a given size, and in particular a length.
  • the annular type combustion chamber (3) has a double inner envelope formed by a sheath (30) (“liner” in English) and a wall (31).
  • the sheath (30) and the wall (31) define a tubular volume for circulation of the air flow coming from the exchanger (1).
  • An outer wall (32) and the wall 31 define a tubular volume of air circulation coming from the compressor (2) and going towards the exchanger (1).
  • the injector (35) passes through these three walls (30 to 32) through three ports.
  • the walls (30 to 32) as well as the tube (35) of the injector are subjected to longitudinal and radial expansions. Fixation is ensured by a combination of connections avoiding hyperstatic situations.
  • connection between the tube (35) of the injector and the interior wall (30) is ensured by a slide connection formed by a calibrated lumen defining with the exterior surface of the tube (35) a calibrated annular clearance.
  • connection between the tube (35) of the injector and the intermediate wall (31) is ensured by a fixed connection.
  • the first alternative embodiment does not conform to the invention as defined by the claims and is illustrated schematically by the figure 2 .
  • the second alternative embodiment does not conform to the invention as defined by the claims and is illustrated schematically by the Figure 3 .
  • the third alternative embodiment does not conform to the invention as defined by the claims and is illustrated schematically by the figure 4 .
  • the fourth alternative embodiment does not conform to the invention as defined by the claims and is illustrated schematically by the figure 5 .
  • connection between said peripheral tube and the intermediate wall (31) of the sheath is constituted by a connection (80) having several degrees of freedom to allow axial movement and tangential movement of the tube, and a tolerance for pivoting.
  • connection between the peripheral tube (30) and the outer wall (32) of the sheath is constituted by a rigid sealed assembly.
  • the outer wall (32) is crossed by a cable gland (37) into which the head (38) of the injector (35) is inserted.
  • This head (38) has a disc collar (38) engaged between the two parts of the gland (37) which ensures tightening and sealing of this disc collar (38).
  • the inner end (40) passes through the inner wall (30) through a simple hole formed in the wall (30).
  • This hole is oblong in this case, to take into account the inclination of the axis of the injector (35) relative to the radial axis.
  • connection between the injector (35) and the intermediate wall (31) is made by a part having a conical upper part (41) flared outwards, extended at its base by a disc flange (42) movable in radial translation in a slot (42) formed in the head (44) of a tubular extension (43) welded to the surface of the interior wall (30).
  • the disc flange (42) is flexible, which also allows slight rotation in relation to this tubular extension (43).

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Joints Allowing Movement (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)

Description

Domaine de l'inventionField of the invention

La présente invention concerne le domaine des turbines à cycle régénératif destinées notamment à la production d'énergie électrique ou mécanique embarquée à partir de carburants pour véhicules aéronautiques, terrestres, maritimes et unités mobiles légères.The present invention relates to the field of regenerative cycle turbines intended in particular for the production of on-board electrical or mechanical energy from fuels for aeronautical, land, maritime vehicles and light mobile units.

Une turbine est composée de trois éléments :

  • un compresseur, qui a pour rôle de comprimer de l'air ambiant à une pression comprise entre 2 et 30 bars environ ;
  • une chambre de combustion, dans laquelle un combustible est injecté sous pression, puis brûlé avec l'air comprimé, avec un fort excès d'air afin de limiter la température des gaz d'échappement ;
  • une turbine axiale dans laquelle sont détendus les gaz qui sortent de la chambre de combustion.
A turbine is made up of three elements:
  • a compressor, which has the role of compressing ambient air to a pressure of between approximately 2 and 30 bars;
  • a combustion chamber, in which a fuel is injected under pressure, then burned with compressed air, with a large excess of air in order to limit the temperature of the exhaust gases;
  • an axial turbine in which the gases leaving the combustion chamber are expanded.

Dans une turbine à cycle régénératif, les gaz d'échappement sortent de la turbine à des températures élevées (supérieures à 500°C), alors que la température de l'air sortant du compresseur est plus basse (typiquement entre 200°C et 400°C), avec une circulation à travers un échangeur de chaleur inséré entre les gaz d'échappement et l'air comprimé permettant de réchauffer partiellement l'air avant entrée dans la chambre de combustion, ce qui permet de réduire la consommation de combustible.In a regenerative cycle turbine, the exhaust gases exit the turbine at high temperatures (above 500°C), while the temperature of the air leaving the compressor is lower (typically between 200°C and 400°C). °C), with circulation through a heat exchanger inserted between the exhaust gases and the compressed air allowing the air to be partially heated before entering the combustion chamber, which reduces fuel consumption.

L'invention concerne plus particulièrement la chambre de combustion et l'injection de combustible dans la chambre de combustion.The invention relates more particularly to the combustion chamber and the injection of fuel into the combustion chamber.

Etat de la techniqueState of the art

Le brevet américain US4453384 décrit un exemple de turbine à gaz comprenant:

  • un boîtier annulaire ayant une pluralité de trous équidistants disposés circonférentiellement; un tube à flamme annulaire positionné coaxialement à l'intérieur et espacé dudit boîtier annulaire,
  • ledit tube à flamme annulaire ayant un nombre correspondant de trous circonférentiellement équidistants alignés coaxialement avec les trous dudit boîtier
  • une pluralité de tubes s'étendant radialement à travers ledit tube de flamme annulaire, chaque tube étant coaxial avec le trou correspondant dans le tube de flamme annulaire et le trou correspondant dans le boîtier annulaire, chaque tube s'étendant perpendiculairement à un axe dudit tube de flamme annulaire, chaque tube ayant un conduit s'étendant à travers celui-ci avec un axe normal à l'axe du tube et parallèle à l'axe dudit tube à flamme annulaire.
The American patent US4453384 describes an example of a gas turbine comprising:
  • an annular housing having a plurality of circumferentially arranged equidistant holes; an annular flame tube positioned coaxially inside and spaced from said annular housing,
  • said annular flame tube having a corresponding number of circumferentially equidistant holes aligned coaxially with the holes of said housing
  • a plurality of tubes extending radially through said annular flame tube, each tube being coaxial with the corresponding hole in the annular flame tube and the corresponding hole in the annular housing, each tube extending perpendicular to an axis of said tube annular flame tube, each tube having a conduit extending therethrough with an axis normal to the axis of the tube and parallel to the axis of said annular flame tube.

On connait aussi le brevet allemand DE1254911 proposant des buses d'injection en forme de crochet montées dans le corps de buse d'injection, qui est fixé dans le porte-flamme avec son embout de buse, de manière à être déplaçable par rapport aux parois de la chambre de combustion.We also know the German patent DE1254911 providing hook-shaped injection nozzles mounted in the injection nozzle body, which is fixed in the flame holder with its nozzle tip, so as to be movable relative to the walls of the combustion chamber.

Dans un mode de réalisation, la partie extérieure du corps de buse d'injection en forme de crochet est montée coulissante dans un guide, éventuellement associé à la paroi extérieure de la chambre de combustion, et un dispositif de serrage dirigé parallèlement à l'embout buccal de la buse est prévu pour maintenir l'extrémité avant de l'embout buccal contre une butée fixée dans un moyeu du porte-flamme.In one embodiment, the exterior part of the hook-shaped injection nozzle body is slidably mounted in a guide, possibly associated with the exterior wall of the combustion chamber, and a clamping device directed parallel to the tip mouthpiece of the nozzle is designed to hold the front end of the mouthpiece against a stop fixed in a hub of the flame holder.

On connaît enfin la demande de brevet britannique GB2097112 décrivant un rûleur à carburant pour moteur à turbine à gaz comprenant un bras d'alimentation en carburant et un injecteur de carburant, le bras d'alimentation en carburant et l'injecteur de carburant étant réunis, le bras d'alimentation en carburant ayant au moins un passage de carburant, l'injecteur de carburant 65 comprenant un corps ayant un passage dans communication avec l'au moins un passage de carburant dans le bras d'alimentation en carburant, le corps ayant un conduit d'air, l'axe du conduit d'air étant coaxial avec l'axe de l'injecteur de carburant, l'injecteur de carburant ayant un ou plusieurs 70 passages de carburant pour injecter du carburant dans le conduit d'air, le brûleur de carburant ayant des moyens de localisation à l'extrémité adjacente à l'injecteur de carburant, les moyens de localisation étant agencés pour s'engager avec des moyens de localisation correspondants sur un composant de moteur.We finally know the British patent application GB2097112 describing a fuel burner for a gas turbine engine comprising a fuel supply arm and a fuel injector, the fuel supply arm and the fuel injector being joined together, the fuel supply arm having at at least one fuel passage, the fuel injector 65 comprising a body having a passage in communication with the at least one fuel passage in the fuel supply arm, the body having an air conduit, the axis of the air conduit being coaxial with the axis of the fuel injector, the fuel injector having one or more fuel passages for injecting fuel into the air conduit, the fuel burner having means for locating at the end adjacent to the fuel injector, the locating means being arranged to engage with corresponding locating means on an engine component.

Inconvénients de l'art antérieurDisadvantages of the prior art

Le problème posé par les solutions de l'art antérieur concerne les turbines présentant une chambre de combustion isolée de l'extérieur par une double paroi, deux parois définissant un conduit annulaire pour la circulation d'un flux d'air comprimé issue du compresseur et la troisième paroi étant la paroi extérieure de la chambre de combustion, permettant la circulation du même flux d'air réchauffé préalablement à la traversée d'un échangeur thermique. Le ou les injecteurs doivent traverser les trois parois de manière étanche ou à tout le moins avec une fuite contrôlée. Cela se traduit par un montage hyperstatique qui ne permet pas d'absorber les dilatations thermiques longitudinales de l'injecteur, ni les dilatations thermiques radiales et longitudinales des parois métalliques soumises à des températures fortement différenciées.The problem posed by the solutions of the prior art concerns turbines having a combustion chamber isolated from the outside by a double wall, two walls defining an annular conduit for the circulation of a flow of compressed air coming from the compressor and the third wall being the exterior wall of the combustion chamber, allowing the circulation of the same flow of air heated before passing through a heat exchanger. The injector(s) must pass through the three walls in a sealed manner or at the very least with a controlled leak. This results in a hyperstatic assembly which does not make it possible to absorb the longitudinal thermal expansions of the injector, nor the radial and longitudinal thermal expansions of the metal walls subjected to strongly differentiated temperatures.

Par ailleurs, dans la solution décrite dans le brevet US4453384 , l'injecteur traverse les parois de la chambre de combustion par des trous simples, référencés 38, 48 et 52. Ce document de l'art antérieur propose de positionner l'injecteur coaxialement à l'intérieur de chacun des trous coaxiaux 52, 48 et 38 prévus dans le boîtier 50. Cette solution conduit donc à de multiples inconvénients : d'une part, la dilatation radiale de l'injecteur est différente de la dilatation surfacique des parois, ce qui conduit soit à des fuites entre la périphérie de l'injecteur et le bord des trous de passage dans la paroi, soit à des serrements du bords des trous autour de la paroi de l'injecteur, ce qui limite les possibilités de déplacement radiaux et peut conduire à des déformations et à une fatigue des parois.Furthermore, in the solution described in the patent US4453384 , the injector passes through the walls of the combustion chamber through simple holes, referenced 38, 48 and 52. This document of the prior art proposes to position the injector coaxially inside each of the coaxial holes 52, 48 and 38 provided in the housing 50. This solution therefore leads to multiple disadvantages: on the one hand, the radial expansion of the injector is different from the surface expansion of the walls, which leads either to leaks between the periphery of the injector and the edge of the passage holes in the wall, or to tightness of the edges of the holes around the wall of the injector, which limits the possibilities of radial movement and can lead to deformation and fatigue of the walls .

Solution apportée par l'inventionSolution provided by the invention

Afin de répondre à ce problème, la présente invention concerne une chambre de combustion d'une turbomachine selon l'objet de la revendication 1.In order to respond to this problem, the present invention relates to a combustion chamber of a turbomachine according to the subject of claim 1.

Des variantes de réalisation sont décrites par les revendications dépendantes.Alternative embodiments are described by the dependent claims.

L'invention sera mieux comprise à la lecture de la description qui suit, concernant un exemple non limitatif de réalisation illustré par les dessins annexés où :

  • les figures 1 à 5 représentent des vues schématiques de variantes de réalisation qui ne sont pas conformes à l'invention telle que définie par les revendications;
  • les figures 6-8 représentent des vues schématique d'une chambre de combustion selon l'invention telle que définie par les revendications.
The invention will be better understood on reading the description which follows, concerning a non-limiting example of embodiment illustrated by the appended drawings where:
  • THE figures 1 to 5 represent schematic views of alternative embodiments which do not conform to the invention as defined by the claims;
  • THE figures 6-8 represent schematic views of a combustion chamber according to the invention as defined by the claims.

La figure 1 décrit une configuration ne faisant pas partie de l'invention telle que définie par les revendications et représente une vue en perspective de la turbomachine, comprenant un échangeur (1), un compresseur (2), une chambre de combustion (3) et une turbine (4). Un déflecteur conique (11) coaxial avec l'échangeur (1) fait circuler les gaz chauds issus de la turbine (4) en direction d'une sortie d'évacuation (12) après avoir traversé l'échangeur (2), en traversant deux cassettes (5, 6) entre les tubes.There figure 1 describes a configuration not forming part of the invention as defined by the claims and represents a perspective view of the turbomachine, comprising an exchanger (1), a compressor (2), a combustion chamber (3) and a turbine (4). A conical deflector (11) coaxial with the exchanger (1) circulates the hot gases coming from the turbine (4) towards an evacuation outlet (12) after passing through the exchanger (2), crossing two cassettes (5, 6) between the tubes.

Les parties constituées par le compresseur (2), la chambre de combustion (3) et la turbine (4) sont connues de l'homme du métier, et conformes à l'état des connaissances en matière de turbomachines.The parts consisting of the compressor (2), the combustion chamber (3) and the turbine (4) are known to those skilled in the art, and conform to the state of knowledge in turbomachinery.

L'échangeur (2) est constitué par un échangeur à tubes, comprenant deux cassettes annulaires (5, 6) coaxiales.The exchanger (2) consists of a tube exchanger, comprising two coaxial annular cassettes (5, 6).

La cassette extérieure (5) est constituée par un assemblage de tubes parallèles, en alliage métallique résistant aux hautes températures, par exemple de l'acier inoxydable réfractaire 347.The outer cassette (5) is made up of an assembly of parallel tubes, made of a metal alloy resistant to high temperatures, for example refractory stainless steel 347.

A titre d'exemple, cette cassette extérieure (5) est constituée de 2000 tubes d'une longueur de 300 millimètres, d'une section intérieure de 2,8 millimètres et de section extérieure de 3 millimètres. Les tubes sont maintenus de manière connue par des intercalaires pour définir des passages des gaz chauds provenant de la turbine.For example, this exterior cassette (5) is made up of 2000 tubes with a length of 300 millimeters, an interior section of 2.8 millimeters and an exterior section of 3 millimeters. The tubes are held in a known manner by spacers to define passages for hot gases coming from the turbine.

Les tubes forment un manchon d'un rayon extérieur de 158 millimètres et d'un rayon intérieur de 128 millimètres.The tubes form a sleeve with an outer radius of 158 millimeters and an inner radius of 128 millimeters.

La cassette intérieure (6) est constituée de 2000 tubes d'une longueur de 300 millimètres, d'une section intérieure de 2,8 millimètres et de section extérieure de 3 millimètres.The inner cassette (6) is made up of 2000 tubes with a length of 300 millimeters, an inner section of 2.8 millimeters and an outer section of 3 millimeters.

Les tubes forment un manchon d'un rayon extérieur de 123 millimètres et d'un rayon intérieur de 67 millimètres.The tubes form a sleeve with an outer radius of 123 millimeters and an inner radius of 67 millimeters.

Les deux cassettes (5, 6) sont coaxiales et encastrée l'une dans l'autre.The two cassettes (5, 6) are coaxial and embedded one inside the other.

Ces deux cassettes (5, 6) sont réunies, à l'extrémité opposées au compresseur (1), par une structure de fermeture annulaire (8).These two cassettes (5, 6) are joined, at the end opposite the compressor (1), by an annular closing structure (8).

Chacune des cassettes (5, 6) comporte, à chaque extrémité, une plaque d'étanchéité frontale percée pour le passage des tubes, et assurant l'entraxe constant des tubes. Les tubes sont brasés ou soudés pour assurer l'étanchéité au niveau de leur raccordement avec les plaques frontales.Each of the cassettes (5, 6) comprises, at each end, a front sealing plate pierced for the passage of the tubes, and ensuring the constant center distance of the tubes. The tubes are brazed or welded to ensure tightness at their connection with the front plates.

Cette structure de fermeture (8) est constituée de deux pièces coaxiales emboîtées, présentant la forme générale d'un moule à baba au rhum, en acier inoxydable réfractaire 347 d'une épaisseur de 2 millimètres.This closing structure (8) is made up of two coaxial interlocking parts, having the general shape of a rum baba mold, in refractory stainless steel 347 with a thickness of 2 millimeters.

La pièce extérieure (9) présente une section extérieure correspondant à la section extérieure de la cassette extérieure (5) et une section intérieure correspondant à la section intérieure de la cassette intérieure (6).The outer part (9) has an outer section corresponding to the outer section of the outer cassette (5) and an inner section corresponding to the inner section of the inner cassette (6).

La pièce intérieure (10) présente une section extérieure correspondant à la section intérieure de la cassette extérieure (5) et une section intérieure correspondant à la section extérieure de la cassette intérieure (6).The inner part (10) has an outer section corresponding to the inner section of the outer cassette (5) and an inner section corresponding to the outer section of the inner cassette (6).

Chacune des pièces (9, 10) présente une symétrie de révolution selon l'axe de la turbomachine, avec une section longitudinale constante.Each of the parts (9, 10) has a symmetry of revolution along the axis of the turbomachine, with a constant longitudinal section.

La structure de fermeture (8) assure la déflexion des gaz provenant de la cassette extérieure (5) vers les tubes constituant la cassette intérieure (6).The closing structure (8) ensures the deflection of gases coming from the outer cassette (5) towards the tubes constituting the inner cassette (6).

Cette solution assure un double passage des gaz dans l'échangeur (1), ce qui augmente significativement son efficacité thermique pour un encombrement, et notamment une longueur, donné.This solution ensures a double passage of gases in the exchanger (1), which significantly increases its thermal efficiency for a given size, and in particular a length.

La chambre de combustion (3) de type annulaire présente une doubleenveloppe intérieure formée par un fourreau (30) (« liner » en anglais ») et une paroi (31). Le fourreau (30) et la paroi (31) définissent un volume tubulaire de circulation du flux d'air issue de l'échangeur (1). Une paroi extérieure (32) et la paroi 31 définissent un volume tubulaire de circulation d'air issue du compresseur (2) et allant vers l'échangeur (1).The annular type combustion chamber (3) has a double inner envelope formed by a sheath (30) (“liner” in English) and a wall (31). The sheath (30) and the wall (31) define a tubular volume for circulation of the air flow coming from the exchanger (1). An outer wall (32) and the wall 31 define a tubular volume of air circulation coming from the compressor (2) and going towards the exchanger (1).

L'injecteur (35) traverse ces trois parois (30 à 32) à travers trois lumières. Les parois (30 à 32) ainsi que le tube (35) de l'injecteur sont soumis à des dilatations longitudinales et radiales. La fixation est assurée par une combinaison de liaisons évitant les situations hyperstatiques.The injector (35) passes through these three walls (30 to 32) through three ports. The walls (30 to 32) as well as the tube (35) of the injector are subjected to longitudinal and radial expansions. Fixation is ensured by a combination of connections avoiding hyperstatic situations.

La liaison entre le tube (35) de l'injecteur et la paroi extérieure (32) est assurée par un soufflet (36) cylindrique.The connection between the tube (35) of the injector and the exterior wall (32) is ensured by a cylindrical bellows (36).

La liaison entre le tube (35) de l'injecteur et la paroi intérieure (30) est assurée par un liaison glissière formée par une lumière calibrée définissant avec la surface extérieure du tube (35) un jeu annulaire calibrée.The connection between the tube (35) of the injector and the interior wall (30) is ensured by a slide connection formed by a calibrated lumen defining with the exterior surface of the tube (35) a calibrated annular clearance.

La liaison entre le tube (35) de l'injecteur et la paroi intermédiaire (31) est assurée par une liaison fixe.The connection between the tube (35) of the injector and the intermediate wall (31) is ensured by a fixed connection.

Première variante de réalisationFirst variant of realization

La première variante de réalisation n'est pas conforme à l'invention telle que définie par les revendications et est illustrée schématiquement par la figure 2.The first alternative embodiment does not conform to the invention as defined by the claims and is illustrated schematically by the figure 2 .

Le tube (35) de l'injecteur traverse les trois parois (30 à 31), avec des liaisons respectivement :

  • Une liaison rotule (42) pour le passage à travers la paroi extérieure (32)
  • Une liaison rotule-glissière (41) pour le passage à travers la paroi intermédiaire (31)
  • Une liaison libre avec un jeu périphérique calibré (40) pour le passage à travers la paroi intérieure (30).
The tube (35) of the injector passes through the three walls (30 to 31), with connections respectively:
  • A ball joint (42) for passage through the exterior wall (32)
  • A ball-slide connection (41) for passage through the intermediate wall (31)
  • A free connection with calibrated peripheral clearance (40) for passage through the interior wall (30).

Deuxième variante de réalisationSecond embodiment variant

La deuxième variante de réalisation n'est pas conforme à l'invention telle que définie par les revendications et est illustrée schématiquement par la figure 3.The second alternative embodiment does not conform to the invention as defined by the claims and is illustrated schematically by the Figure 3 .

Le tube (35) de l'injecteur traverse les trois parois (30 à 31), avec des liaisons respectivement :

  • Une liaison rotule-glissière (52) pour le passage à travers la paroi extérieure (32)
  • Une liaison rotule (51) pour le passage à travers la paroi intermédiaire (31)
  • Une liaison libre avec un jeu périphérique calibré (50) pour le passage à travers la paroi intérieure (30).
The tube (35) of the injector passes through the three walls (30 to 31), with connections respectively:
  • A ball joint-slide connection (52) for passage through the exterior wall (32)
  • A ball joint (51) for passage through the intermediate wall (31)
  • A free connection with calibrated peripheral clearance (50) for passage through the interior wall (30).

Troisième variante de réalisationThird alternative embodiment

La troisième variante de réalisation n'est pas conforme à l'invention telle que définie par les revendications et est illustrée schématiquement par la figure 4.The third alternative embodiment does not conform to the invention as defined by the claims and is illustrated schematically by the figure 4 .

Le tube (35) de l'injecteur traverse les trois parois (30 à 31), avec des liaisons respectivement :

  • Un soufflet (62) pour le passage à travers la paroi extérieure (32)
  • Une liaison soudée (61) pour le passage à travers la paroi intermédiaire (31)
  • Une liaison libre avec un jeu périphérique calibré (60) pour le passage à travers la paroi intérieure (30).
The tube (35) of the injector passes through the three walls (30 to 31), with connections respectively:
  • A bellows (62) for passage through the outer wall (32)
  • A welded connection (61) for passage through the intermediate wall (31)
  • A free connection with calibrated peripheral clearance (60) for passage through the interior wall (30).

Quatrième variante de réalisationFourth embodiment

La quatrième variante de réalisation n'est pas conforme à l'invention telle que définie par les revendications et est illustrée schématiquement par la figure 5.The fourth alternative embodiment does not conform to the invention as defined by the claims and is illustrated schematically by the figure 5 .

Le tube (35) de l'injecteur traverse les trois parois (30 à 31), avec des liaisons respectivement :

  • Une liaison soudée (72) pour le passage à travers la paroi extérieure (32)
  • Un soufflet tronconique métallique (71) pour le passage à travers la paroi intermédiaire (31)
  • Une liaison libre avec un jeu périphérique calibré (70) pour le passage à travers la paroi intérieure (30).
The tube (35) of the injector passes through the three walls (30 to 31), with connections respectively:
  • A welded connection (72) for passage through the exterior wall (32)
  • A frustoconical metal bellows (71) for passage through the intermediate wall (31)
  • A free connection with calibrated peripheral clearance (70) for passage through the interior wall (30).

Réalisation selon l'inventionProduction according to the invention

La configuration selon l'invention telle que définie par les revendications est illustrée schématiquement par les figures 6 à 8.The configuration according to the invention as defined by the claims is illustrated schematically by the figures 6 to 8 .

Le tube de l'injecteur (35) traverse les trois parois (30 à 31), avec des liaisons respectivement :

  • Une liaison soudée (72) pour le passage à travers la paroi extérieure (32)
  • Une liaison multidirectionnelle (80) pour le passage à travers la paroi intermédiaire (31)
  • Une liaison libre avec un jeu périphérique calibré (70) pour le passage à travers la paroi intérieure (30).
The injector tube (35) passes through the three walls (30 to 31), with connections respectively:
  • A welded connection (72) for passage through the exterior wall (32)
  • A multidirectional connection (80) for passage through the intermediate wall (31)
  • A free connection with calibrated peripheral clearance (70) for passage through the interior wall (30).

La liaison entre ledit tube périphérique et la paroi intermédiaire (31) du fourreau est constituée par une liaison (80) présentant plusieurs degrés de liberté pour permettre un déplacement axial et un déplacement tangentiel du tube, et une tolérance pour un rotulage.The connection between said peripheral tube and the intermediate wall (31) of the sheath is constituted by a connection (80) having several degrees of freedom to allow axial movement and tangential movement of the tube, and a tolerance for pivoting.

La liaison entre le tube périphérique (30) et la paroi extérieure (32) du fourreau est constituée par assemblage étanche rigide.The connection between the peripheral tube (30) and the outer wall (32) of the sheath is constituted by a rigid sealed assembly.

La paroi extérieure (32) est traversée par un presse-étoupe (37) dans lequel est inséré la tête (38) de l'injecteur (35). Cette tête (38) présente une collerette discale (38) engagée entre les deux parties du presse-étoupe (37) qui assure un serrage et une étanchéité de cette collerette discale (38).The outer wall (32) is crossed by a cable gland (37) into which the head (38) of the injector (35) is inserted. This head (38) has a disc collar (38) engaged between the two parts of the gland (37) which ensures tightening and sealing of this disc collar (38).

L'extrémité intérieure (40) traverse la paroi intérieure (30) par le passage dans un simple trou formé dans la paroi (30). Ce trou est oblong dans le cas d'espèce, pour prendre en compte l'inclinaison de l'axe de l'injecteur (35) par rapport à l'axe radial.The inner end (40) passes through the inner wall (30) through a simple hole formed in the wall (30). This hole is oblong in this case, to take into account the inclination of the axis of the injector (35) relative to the radial axis.

La liaison entre l'injecteur (35) et la paroi intermédiaire (31) est réalisée par une pièce présente une partie supérieure (41) conique évasée vers l'extérieur, prolongée à sa base par une collerette discale (42) mobile en translation radiale dans une fente (42) formée dans la tête (44) d'un prolongement tubulaire (43) soudé à la surface de la paroi intérieure (30).The connection between the injector (35) and the intermediate wall (31) is made by a part having a conical upper part (41) flared outwards, extended at its base by a disc flange (42) movable in radial translation in a slot (42) formed in the head (44) of a tubular extension (43) welded to the surface of the interior wall (30).

La collerette discale (42) est flexible, ce qui permet par ailleurs un léger rotulage par rapport à ce prolongement tubulaire (43).The disc flange (42) is flexible, which also allows slight rotation in relation to this tubular extension (43).

Claims (4)

  1. - A combustion chamber for a turbine engine, comprising two coaxial rotationally symmetrical walls comprising an inner wall (30) and an intermediate wall (31) extending one inside the other and delimiting between them an annular space (33) for circulating air, and an outer wall (32), and at least one injector (35) passing through said inner wall (30), intermediate wall (31) and outer wall (32) via apertures, characterized in that said at least one injector (35) has a peripheral tube connected to said walls (30 to 32) by means of three connections, wherein a connection between the peripheral tube and the outer wall (32) is formed by a rigid sealed assembly, wherein a connection between the peripheral tube and the intermediate wall (31) is achieved using a part having an outwardly flared conical upper portion (41), extended at its base by means of a disk collar (42) which is movable in radial translation in a slot (42) formed in the head (44) of a tubular extension (43) welded to the surface of the intermediate wall (31), at least two of the connections being sealed flexible connections.
  2. - The combustion chamber for a turbine engine according to claim 1, characterized in that the connection between said peripheral tube (35) and the inner wall (30) is formed by an annular linear connection with leakage controlled by a calibrating annular section.
  3. - The combustion chamber for a turbine engine according to claim 1, characterized in that said outer wall (32) is traversed by a gland (37) into which the head (38) of the injector (35) is inserted, said head (38) having a disk collar (38) inserted between the two portions of the gland (37).
  4. - The combustion chamber for a turbine engine according to claim 1, characterized in that the inner end (40) of the injector (35) passes through the inner wall (30) via the passage in an oblong hole formed in the inner wall (30).
EP19845596.6A 2018-12-21 2019-12-17 Turbomachine combustion chamber Active EP3899371B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1874016A FR3090747B1 (en) 2018-12-21 2018-12-21 Combustion chamber of a turbomachine
PCT/FR2019/053108 WO2020128292A1 (en) 2018-12-21 2019-12-17 Turbomachine combustion chamber

Publications (3)

Publication Number Publication Date
EP3899371A1 EP3899371A1 (en) 2021-10-27
EP3899371C0 EP3899371C0 (en) 2024-02-07
EP3899371B1 true EP3899371B1 (en) 2024-02-07

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US (1) US20220074595A1 (en)
EP (1) EP3899371B1 (en)
CN (1) CN113454390B (en)
CA (1) CA3124209A1 (en)
FR (1) FR3090747B1 (en)
WO (1) WO2020128292A1 (en)

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Publication number Publication date
EP3899371C0 (en) 2024-02-07
WO2020128292A1 (en) 2020-06-25
FR3090747A1 (en) 2020-06-26
US20220074595A1 (en) 2022-03-10
CN113454390B (en) 2023-02-24
FR3090747B1 (en) 2021-01-22
EP3899371A1 (en) 2021-10-27
CA3124209A1 (en) 2020-06-25
CN113454390A (en) 2021-09-28

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