EP1873458B1 - Arrangement for a gas turbine combustion chamber having a deflector with flange - Google Patents

Arrangement for a gas turbine combustion chamber having a deflector with flange Download PDF

Info

Publication number
EP1873458B1
EP1873458B1 EP07110586A EP07110586A EP1873458B1 EP 1873458 B1 EP1873458 B1 EP 1873458B1 EP 07110586 A EP07110586 A EP 07110586A EP 07110586 A EP07110586 A EP 07110586A EP 1873458 B1 EP1873458 B1 EP 1873458B1
Authority
EP
European Patent Office
Prior art keywords
bowl
deflector
annular
end wall
injector system
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.)
Active
Application number
EP07110586A
Other languages
German (de)
French (fr)
Other versions
EP1873458A1 (en
Inventor
David Locatelli
Romain Lunel
Thomas Noel
Denis Sandelis
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1873458A1 publication Critical patent/EP1873458A1/en
Application granted granted Critical
Publication of EP1873458B1 publication Critical patent/EP1873458B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • F23D—BURNERS
    • F23D2211/00—Thermal dilatation prevention or compensation

Definitions

  • the present invention relates to the general field of turbomachine combustion chambers. It relates more particularly to an arrangement of a combustion chamber of the type comprising a chamber bottom pierced with at least one circular opening, an injection system associated with the opening and a deflector mounted on the downstream side of the chamber bottom in the opening.
  • annular turbomachine combustion chamber comprises two longitudinal annular walls (an inner wall and an outer wall) which are connected at their respective upstream end by an equally annular transverse wall forming a chamber bottom. It is provided with a plurality of regularly spaced circular openings and in which are mounted systems for injecting an air / fuel mixture to be burned inside the combustion chamber.
  • the fuel is supplied to the injection systems via injectors integral with the turbomachine casing and whose heads are centered on the injection systems.
  • the air it is introduced into each injection system by means of one or more air spirals opening downstream of the head of the fuel injector.
  • a flared bowl downstream is mounted in each opening to ensure a good distribution of the air / fuel mixture in the primary zone of the combustion chamber.
  • a deflector mounted in each opening of the bottom chamber of the downstream side thereof provides thermal protection of the chamber bottom against the high temperatures of the gases from the combustion of the air / fuel mixture in the combustion chamber.
  • the bowl of the injection system with a flange which projects into the interior of the chamber bottom and which extends parallel thereto.
  • a collar has the main function of protecting the injection system against combustion flames in case of decentering of the injection system relative to the chamber bottom.
  • the collar of the bowl which must pass through the opening of the chamber bottom necessarily has a diameter smaller than that of the opening.
  • the main purpose of the present invention is therefore to overcome such drawbacks by proposing an arrangement for a turbomachine combustion chamber which makes it possible to effectively protect the injection system against combustion flames regardless of the decentering of the injection system with respect to the room bottom, while ensuring none of its component parts fall into the combustion chamber in the event of breakage of solder or solder.
  • a turbomachine combustion chamber comprising a chamber bottom pierced with at least one substantially circular opening, a deflector mounted on the downstream side of the chamber bottom in the opening via an annular sheath, an injection system associated with the opening and having a downwardly flared annular bowl which passes through the opening, the bowl of the injection system having at its downstream end an annular groove open towards the outside , and means for allowing an off-centering of the injection system with respect to the chamber bottom, and wherein, in accordance with the invention, the deflector comprises an annular flange extending radially inwards and the annular groove is aligned radially with the flange of the deflector so that it can retract into said groove in case of decentering of the injection system relative to the chamber bottom.
  • all the constituent parts of the injection system may be of diameter greater than that of the opening of the chamber bottom and mounted upstream, which ensures that none of these parts can pass through the opening and fall inside the combustion chamber especially in case of solder or defective welding.
  • the annular groove of the bowl is formed of two axially spaced lateral walls connected by an annular bottom, the distance between said side walls of the groove being greater than the thickness of the flange of the deflector. so as to allow a circulation of the ventilation air regardless of the decentering of the injection system relative to the chamber bottom.
  • the means making it possible to allow an off-centering of the injection system with respect to the chamber bottom consist of a clamping ring mounted on the upstream side of the chamber bottom and fixed against the sheath. with which they define an open annular groove on the axis side the opening of the chamber bottom, the bowl of the injection system further comprising an annular flange adapted to slide radially in the groove formed by the clamping ring and the sleeve.
  • the flange of the bowl is extended downstream by a substantially cylindrical portion which connects to the groove by an annular shoulder.
  • the shoulder of the bowl is advantageously pierced with a plurality of ventilation holes opening on the upstream side of the chamber bottom and opening on the downstream side thereof facing the flange of the deflector.
  • the radial height of the flange of the deflector is preferably at least equal to that of the flange of the bowl so as to protect the injection system regardless of the decentering of the injection system by compared to the chamber bottom.
  • the injection system further comprises at least one air swirler fixed to the upstream end of the bowl and a centering ring attached to the upstream end of the swirler. air and surrounding a fuel injector.
  • the invention also relates to a combustion chamber and a turbomachine comprising an arrangement as defined above.
  • FIG. 1 to 3 partially represent a sectional view of a turbomachine combustion chamber 2 equipped with an arrangement according to the invention.
  • such a combustion chamber 2 is formed of an inner longitudinal annular wall and an outer longitudinal annular wall (these walls are not represented on the figure 1 ), these walls being connected at their respective upstream end by a transverse annular wall 4 forming chamber bottom.
  • the chamber bottom 4 has an upstream side 4a and a downstream side 4b, the latter being directed towards the inside of the combustion chamber 2.
  • the chamber bottom is pierced with a plurality of openings 6 which are regularly spaced apart and each having a substantially circular shape of axis XX.
  • An injection system 8 of an air / fuel mixture is associated with each of these openings 6.
  • a deflector 10 protecting the chamber bottom 4 of the combustion flames is also mounted in each of the openings 6 on the downstream side 4b of the chamber bottom via an annular sleeve 12 projecting from the upstream side.
  • the deflector 10 has an annular flange 14 which extends radially inwards (that is to say towards the X-X axis of the opening 6 of the chamber bottom). As explained later, this flange 14 of the baffle has the role of protecting the injection system against combustion flames.
  • Each injection system 8 has an axis of revolution Y-Y and consists in particular of a fuel injector integral with the turbomachine casing (not shown in the figures).
  • the head 16 of the injector is disposed on the upstream side 4a of the chamber bottom 4 and is centered on the Y-Y axis of the injection system via a centering ring 18 which surrounds it.
  • One or more air swivels 20 optionally provided with a venturi 22 are attached to the downstream end of the centering ring 18 of the injection system. This or these air swirlers 20 allow air to enter the injection system in a substantially radial direction and to mix with the fuel delivered by the head 16 of the fuel injector. The air / fuel mixture then enters the combustion chamber 2 to be ignited.
  • Each injection system 8 also comprises a so-called pinch ring 24 which is mounted on the upstream side 4a of the chamber bottom 4 and fixed against the sleeve 12 for holding the deflector 10.
  • This pinch ring 24 is centered on the axis XX of the opening 6 of the chamber bottom and defines with the sleeve 12 an annular groove 26 which is open on the side of the axis XX.
  • Each injection system 8 further comprises a bowl 28 fixed against the downstream end of the air swirler 20 and whose function is to ensure a good distribution of the air / fuel mixture in the primary zone of the combustion chamber.
  • the bowl 28 is mounted in the corresponding opening 6 of the chamber bottom 4 and passes therethrough. It is generally in the form of a ring centered on the YY axis of the injection system and terminates at its downstream end by a U-shaped annular groove 30 which is open towards the outside (ie that is to say on the opposite side to the axis XX of the opening of the chamber bottom) and radially aligned with the flange 14 of the deflector 10.
  • the bowl 28 At its upstream end, the bowl 28 comprises an annular flange 32 mounted on the upstream side 4a of the chamber bottom 4 and able to slide radially inside the groove 26 formed between the clamping ring 24 and the sleeve 12 for holding the deflector 10 so as to allow an off-centering of the injection system 8 with respect to the chamber bottom 4.
  • the head 16 of the fuel injector and the entire injection system 8 are slidably mounted relative to the chamber bottom 4 in order to make up for the thermal expansion gaps between the casing and the combustion chamber. With this type of arrangement, the head 16 of the fuel injector therefore remains permanently centered with respect to the injection system 8.
  • the flange 32 of the bowl is extended downstream by a substantially cylindrical portion 34 of smaller diameter than that of the opening 6 and which is connected to the groove 30 by an annular shoulder 36 on the upstream side thereof.
  • the groove 30 is disposed behind an annular flange 38 which extends radially outwards and whose diameter is smaller than that of the shoulder 36.
  • the groove 30 of the bowl is formed of two annular lateral walls which are spaced axially and connected at their inner end by an annular bottom 40, one of these walls 42 being connected at its outer end to the shoulder 36 and the other wall 44 being connected at its outer end to the flange 38.
  • the flange 38 is the part of the bowl which is located furthest downstream. This flange is extended upstream by a portion 46 which is flared downstream, this flared portion 46 extending itself upstream by a cylindrical portion 48 which is concentric with the cylindrical portion 34 of the bowl (and of smaller diameter than this) and is connected to the air swirler 20.
  • the flared portion 46 of the bowl is pierced with a plurality of air introduction holes 50.
  • the shoulder 36 of the bowl is also pierced with a plurality of ventilation holes 52 opening on the upstream side of the chamber bottom 4 and opening on the downstream side thereof facing the collar 14 of the deflector 10.
  • the air flowing through these ventilation holes 52 is cooled by the upstream flange 14 of the baffle, then flows into the groove 30 of the bowl to create a film of air flowing thereafter radially along the downstream side of the deflector 10 so to cool the latter.
  • the figure 2 represents one of the two possible cases of maximum decentering between the injection system and the chamber bottom (the axis of revolution YY of the injection system is shifted radially outwards with respect to the axis XX of the opening of the chamber floor).
  • the radial distance separating the shoulder 36 from the bottom 40 of the groove 30 of the bowl is preferably at least equal to the radial height of the flange 14 of the baffle 10 so that this flange can fully retract into the throat of the bowl.
  • the flange 32 of the injection system which is completely retracted into the groove 26 is thus well protected against combustion flames.
  • the figure 3 represents the other possible case of maximum decentering between the injection system and the chamber bottom (the axis of revolution YY of the injection system is shifted radially inwards with respect to the axis XX of the opening from the bedroom floor).
  • the flange 14 of the baffle 10 continues to perform its role of thermal protection of the injection system against combustion flames by completely covering the flange 32. This is due to the fact that the radial height of the flange 14 of the flange deflector is preferably at least equal to that of the flange 32 of the bowl.
  • the distance separating the lateral walls 42, 44 of the groove 30 of the bowl is greater than the thickness of the collar 14 of the deflector 10 so as to allow a circulation of the ventilation air passing through the holes 52 drilled in the shoulder 36 whatever the decentering of the injection system relative to the chamber bottom. So, in the extreme case of decentering the figure 2 , the ventilation air passing through the holes 52 continues to circulate inside the groove 30 bypassing the flange 14 of the baffle.
  • the assembly of the arrangement according to the invention is carried out as follows.
  • the sleeve 12 for holding the deflector, the bowl 28, the clamping ring 24, the air swirler 20 and the centering ring 18 are mounted upstream (that is to say by the upstream side 4a of the chamber bottom 4) and fixed to each other (soldered or welded for example).
  • the deflector 10 is mounted in the opening 6 of the chamber bottom 4 downstream (that is to say by the downstream side 4b of the chamber bottom) and then fixed to the sheath 12.
  • the flange 14 thereof may have a smaller diameter than the opening 6 of the chamber bottom 4 which is chosen according to the maximum deviations of possible decentering of the system injection in relation to the chamber bottom so as to permanently ensure thermal protection of the injection system against the combustion flames.

Description

Arrière-plan de l'inventionBackground of the invention

La présente invention se rapporte au domaine général des chambres de combustion de turbomachine. Elle vise plus particulièrement un agencement d'une chambre de combustion du type comportant un fond de chambre percé d'au moins une ouverture circulaire, un système d'injection associé à l'ouverture et un déflecteur monté du côté aval du fond de chambre dans l'ouverture.The present invention relates to the general field of turbomachine combustion chambers. It relates more particularly to an arrangement of a combustion chamber of the type comprising a chamber bottom pierced with at least one circular opening, an injection system associated with the opening and a deflector mounted on the downstream side of the chamber bottom in the opening.

De façon générale, une chambre de combustion annulaire de turbomachine comprend deux parois annulaires longitudinales (une paroi interne et une paroi externe) qui sont reliées à leur extrémité amont respective par une paroi transversale également annulaire formant fond de chambre. Celui-ci est muni d'une pluralité d'ouvertures circulaires régulièrement espacées et dans lesquelles sont montés des systèmes d'injection d'un mélange air/carburant destiné à être brûlé à l'intérieur de la chambre de combustion.In general, an annular turbomachine combustion chamber comprises two longitudinal annular walls (an inner wall and an outer wall) which are connected at their respective upstream end by an equally annular transverse wall forming a chamber bottom. It is provided with a plurality of regularly spaced circular openings and in which are mounted systems for injecting an air / fuel mixture to be burned inside the combustion chamber.

Le carburant est fourni aux systèmes d'injection par l'intermédiaire d'injecteurs solidaires du carter de turbomachine et dont les têtes sont centrées sur les systèmes d'injection. Quant à l'air, il est introduit dans chaque système d'injection au moyen d'une ou plusieurs vrilles d'air débouchant en aval de la tête de l'injecteur de carburant. En outre, un bol évasé vers l'aval est monté dans chaque ouverture afin d'assurer une bonne répartition du mélange air/carburant dans la zone primaire du foyer de combustion. Enfin, un déflecteur monté dans chaque ouverture du fond de chambre du côté aval de celui-ci assure une protection thermique du fond de chambre contre les températures élevées des gaz issus de la combustion du mélange air/carburant dans la chambre de combustion.The fuel is supplied to the injection systems via injectors integral with the turbomachine casing and whose heads are centered on the injection systems. As for the air, it is introduced into each injection system by means of one or more air spirals opening downstream of the head of the fuel injector. In addition, a flared bowl downstream is mounted in each opening to ensure a good distribution of the air / fuel mixture in the primary zone of the combustion chamber. Finally, a deflector mounted in each opening of the bottom chamber of the downstream side thereof provides thermal protection of the chamber bottom against the high temperatures of the gases from the combustion of the air / fuel mixture in the combustion chamber.

Des différences de dilatation thermique existent entre le carter de turbomachine dont sont solidaires les injecteurs de carburant et les parois de la chambre de combustion. Afin de rattraper ces écarts de dilatation, il est donc nécessaire de prévoir un certain degré de liberté entre la chambre de combustion et les systèmes d'injection. A cet effet, il peut être prévu de centrer la tête des injecteurs de carburant sur une traversée coulissante pouvant se déplacer radialement par rapport au système d'injection (on se réfèrera par exemple au document FR 2 825 778 ou au document EP 0 833 107 ). Alternativement, dans certaines situations, le défaut de concentricité entre l'injecteur et le système d'injection associé n'est pas acceptable de sorte que le rattrapage des écarts de dilatation doit se faire par coulissement du système d'injection par rapport au fond de chambre. L'invention concerne un agencement de ce dernier type.Differences in thermal expansion exist between the turbomachine casing which are integral with the fuel injectors and the walls of the combustion chamber. In order to make up for these expansion gaps, it is therefore necessary to provide a certain degree of freedom between the combustion chamber and the injection systems. For this purpose, he may be provided to center the head of the fuel injectors on a sliding bushing that can move radially relative to the injection system (reference will be made for example to the document FR 2,825,778 or to the document EP 0 833 107 ). Alternatively, in certain situations, the lack of concentricity between the injector and the associated injection system is not acceptable so that the retraction of the expansion gaps must be made by sliding the injection system relative to the bottom of the nozzle. bedroom. The invention relates to an arrangement of the latter type.

Une autre contrainte d'un tel agencement doit être respectée. En cas de rupture d'une des brasures ou soudures par lesquelles les pièces constitutives de l'agencement sont assemblées, il est en effet impératif d'éviter que l'une de ces pièces se détache et tombe à l'intérieur de la chambre de combustion avec le risque de venir endommager la turbine haute-pression montée en sortie de la chambre. Pour parer à une telle éventualité, il est connu de donner aux pièces constitutives de l'agencement un diamètre supérieur à celui de l'ouverture du fond de chambre et de les monter par le côté amont du fond de chambre.Another constraint of such an arrangement must be respected. In case of breakage of one of the solders or welds by which the constituent parts of the arrangement are assembled, it is indeed imperative to prevent one of these parts from falling off and falling inside the chamber of combustion with the risk of damaging the high-pressure turbine mounted at the outlet of the chamber. To counter such an eventuality, it is known to give the constituent parts of the arrangement a diameter greater than that of the opening of the chamber bottom and to mount them by the upstream side of the chamber bottom.

En outre, il est de pratique courante de munir le bol du système d'injection d'une collerette qui fait saillie à l'intérieur du fond de chambre et qui s'étend parallèlement à celui-ci. Une telle collerette a pour fonction principale de protéger le système d'injection contre les flammes de combustion en cas de décentrage du système d'injection par rapport au fond de chambre. Or, avec un agencement dont les pièces constitutives sont montées par l'amont du fond de chambre, la collerette du bol qui doit traverser l'ouverture du fond de chambre présente nécessairement un diamètre inférieur à celui de l'ouverture. Il en résulte qu'en cas de décentrage important du système d'injection par rapport au fond de chambre, la collerette du bol n'assure plus sa fonction de protection thermique contre les flammes de combustion.In addition, it is common practice to provide the bowl of the injection system with a flange which projects into the interior of the chamber bottom and which extends parallel thereto. Such a collar has the main function of protecting the injection system against combustion flames in case of decentering of the injection system relative to the chamber bottom. However, with an arrangement whose constituent parts are mounted upstream of the chamber bottom, the collar of the bowl which must pass through the opening of the chamber bottom necessarily has a diameter smaller than that of the opening. As a result, in case of significant decentering of the injection system relative to the chamber bottom, the collar of the bowl no longer provides its thermal protection function against combustion flames.

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

La présente invention a donc pour but principal de pallier de tels inconvénients en proposant un agencement pour chambre de combustion de turbomachine qui permet de protéger efficacement le système d'injection contre les flammes de combustion quelque soit le décentrage du système d'injection par rapport au fond de chambre, tout en assurant qu'aucune de ses pièces constitutives ne tombe à l'intérieur de la chambre de combustion en cas de rupture d'une brasure ou soudure.The main purpose of the present invention is therefore to overcome such drawbacks by proposing an arrangement for a turbomachine combustion chamber which makes it possible to effectively protect the injection system against combustion flames regardless of the decentering of the injection system with respect to the room bottom, while ensuring none of its component parts fall into the combustion chamber in the event of breakage of solder or solder.

Ces buts sont atteints grâce à un agencement pour chambre de combustion de turbomachine, comportant un fond de chambre percé d'au moins une ouverture sensiblement circulaire, un déflecteur monté du côté aval du fond de chambre dans l'ouverture par l'intermédiaire d'un fourreau annulaire, un système d'injection associé à l'ouverture et comportant un bol annulaire évasé vers l'aval qui traverse l'ouverture, le bol du système d'injection comportant à son extrémité aval une gorge annulaire ouverte vers l'extérieur, et des moyens permettant d'autoriser un décentrage du système d'injection par rapport au fond de chambre, et dans lequel, conformément à l'invention, le déflecteur comporte une collerette annulaire s'étendant radialement vers l'intérieur et le gorge annulaire est alignée radialement avec la collerette du déflecteur de sorte que celle-ci puisse se rétracter dans ladite gorge en cas de décentrage du système d'injection par rapport au fond de chambre.These objects are achieved by means of an arrangement for a turbomachine combustion chamber, comprising a chamber bottom pierced with at least one substantially circular opening, a deflector mounted on the downstream side of the chamber bottom in the opening via an annular sheath, an injection system associated with the opening and having a downwardly flared annular bowl which passes through the opening, the bowl of the injection system having at its downstream end an annular groove open towards the outside , and means for allowing an off-centering of the injection system with respect to the chamber bottom, and wherein, in accordance with the invention, the deflector comprises an annular flange extending radially inwards and the annular groove is aligned radially with the flange of the deflector so that it can retract into said groove in case of decentering of the injection system relative to the chamber bottom.

La présence de la collerette du déflecteur permet de protéger efficacement le bol du système d'injection contre les flammes de combustion quelque soit le décentrage du système d'injection par rapport au fond de chambre. En outre, avec un tel agencement, toutes les pièces constitutives du système d'injection peuvent être de diamètre supérieur à celui de l'ouverture du fond de chambre et montées par l'amont, ce qui garantit qu'aucune de ces pièces ne peut passer au travers de l'ouverture et tomber à l'intérieur de la chambre de combustion notamment en cas de brasure ou soudure défectueuse.The presence of the flange of the baffle effectively protects the bowl of the injection system against combustion flames whatever the bias of the injection system relative to the chamber bottom. In addition, with such an arrangement, all the constituent parts of the injection system may be of diameter greater than that of the opening of the chamber bottom and mounted upstream, which ensures that none of these parts can pass through the opening and fall inside the combustion chamber especially in case of solder or defective welding.

Selon une disposition avantageuse de l'invention, la gorge annulaire du bol est formée de deux parois latérales espacées axialement et reliées par un fond annulaire, la distance entre lesdites parois latérales de la gorge étant supérieure à l'épaisseur de la collerette du déflecteur de façon à autoriser une circulation de l'air de ventilation quelque soit le décentrage du système d'injection par rapport au fond de chambre.According to an advantageous arrangement of the invention, the annular groove of the bowl is formed of two axially spaced lateral walls connected by an annular bottom, the distance between said side walls of the groove being greater than the thickness of the flange of the deflector. so as to allow a circulation of the ventilation air regardless of the decentering of the injection system relative to the chamber bottom.

Selon une autre disposition avantageuse de l'invention, les moyens permettant d'autoriser un décentrage du système d'injection par rapport au fond de chambre se composent d'une bague de pincement montée du côté amont du fond de chambre et fixée contre le fourreau avec lequel ils définissent une rainure annulaire ouverte du côté de l'axe de l'ouverture du fond de chambre, le bol du système d'injection comportant en outre un flasque annulaire apte à coulisser radialement dans la rainure formée par la bague de pincement et le fourreau.According to another advantageous arrangement of the invention, the means making it possible to allow an off-centering of the injection system with respect to the chamber bottom consist of a clamping ring mounted on the upstream side of the chamber bottom and fixed against the sheath. with which they define an open annular groove on the axis side the opening of the chamber bottom, the bowl of the injection system further comprising an annular flange adapted to slide radially in the groove formed by the clamping ring and the sleeve.

De préférence, le flasque du bol se prolonge en aval par une partie sensiblement cylindrique qui se raccorde à la gorge par un épaulement annulaire. Dans ce cas, l'épaulement du bol est avantageusement percé d'une pluralité de trous de ventilation s'ouvrant du côté amont du fond de chambre et débouchant du côté aval de celui-ci en regard de la collerette du déflecteur.Preferably, the flange of the bowl is extended downstream by a substantially cylindrical portion which connects to the groove by an annular shoulder. In this case, the shoulder of the bowl is advantageously pierced with a plurality of ventilation holes opening on the upstream side of the chamber bottom and opening on the downstream side thereof facing the flange of the deflector.

Selon encore une autre disposition avantageuse de l'invention, la hauteur radiale de la collerette du déflecteur est de préférence au moins égale à celle du flasque du bol de façon à protéger le système d'injection quelque soit le décentrage du système d'injection par rapport au fond de chambre.According to yet another advantageous arrangement of the invention, the radial height of the flange of the deflector is preferably at least equal to that of the flange of the bowl so as to protect the injection system regardless of the decentering of the injection system by compared to the chamber bottom.

Selon encore une autre disposition avantageuse de l'invention, le système d'injection comporte en outre au moins une vrille d'air fixée à l'extrémité amont du bol et une bague de centrage fixée à l'extrémité amont de la vrille d'air et entourant un injecteur de carburant.According to yet another advantageous arrangement of the invention, the injection system further comprises at least one air swirler fixed to the upstream end of the bowl and a centering ring attached to the upstream end of the swirler. air and surrounding a fuel injector.

L'invention a aussi pour objet une chambre de combustion et une turbomachine comportant un agencement tel que défini précédemment.The invention also relates to a combustion chamber and a turbomachine comprising an arrangement as defined above.

Brève description des dessinsBrief description of the drawings

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

  • la figure 1 est une vue partielle et en coupe d'une chambre de combustion comportant un agencement selon l'invention ; et
  • les figures 2 et 3 sont des vues correspondant à la figure 1 dans lesquelles le système d'injection est décentré par rapport au fond de chambre.
Other features and advantages of the present invention will emerge from the description given below, with reference to the accompanying drawings which illustrate an embodiment having no limiting character. In the figures:
  • the figure 1 is a partial view in section of a combustion chamber comprising an arrangement according to the invention; and
  • the Figures 2 and 3 are views corresponding to the figure 1 in which the injection system is off-center with respect to the chamber bottom.

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

Les figures 1 à 3 représentent partiellement une vue en coupe d'une chambre de combustion de turbomachine 2 équipée d'un agencement selon l'invention.The Figures 1 to 3 partially represent a sectional view of a turbomachine combustion chamber 2 equipped with an arrangement according to the invention.

De façon bien connue en soi, une telle chambre de combustion 2 est formée d'une paroi annulaire longitudinale interne et d'une paroi annulaire longitudinale externe (ces parois ne sont pas représentées sur la figure 1), ces parois étant reliées à leur extrémité amont respective par une paroi annulaire transversale 4 formant fond de chambre.In a manner well known per se, such a combustion chamber 2 is formed of an inner longitudinal annular wall and an outer longitudinal annular wall (these walls are not represented on the figure 1 ), these walls being connected at their respective upstream end by a transverse annular wall 4 forming chamber bottom.

Le fond de chambre 4 présente un côté amont 4a et un côté aval 4b, ce dernier étant dirigé vers l'intérieur de la chambre de combustion 2. Le fond de chambre est percé d'une pluralité d'ouvertures 6 qui sont régulièrement espacées et qui présentent chacune une forme sensiblement circulaire d'axe X-X. Un système d'injection 8 d'un mélange air/carburant est associé à chacune de ces ouvertures 6.The chamber bottom 4 has an upstream side 4a and a downstream side 4b, the latter being directed towards the inside of the combustion chamber 2. The chamber bottom is pierced with a plurality of openings 6 which are regularly spaced apart and each having a substantially circular shape of axis XX. An injection system 8 of an air / fuel mixture is associated with each of these openings 6.

Un déflecteur 10 protégeant le fond de chambre 4 des flammes de combustion est également monté dans chacune des ouvertures 6 du côté aval 4b du fond de chambre par l'intermédiaire d'un fourreau annulaire 12 faisant saillie du côté amont.A deflector 10 protecting the chamber bottom 4 of the combustion flames is also mounted in each of the openings 6 on the downstream side 4b of the chamber bottom via an annular sleeve 12 projecting from the upstream side.

Conformément à l'invention, le déflecteur 10 présente une collerette annulaire 14 qui s'étend radialement vers l'intérieur (c'est-à-dire vers l'axe X-X de l'ouverture 6 du fond de chambre). Comme expliqué ultérieurement, cette collerette 14 du déflecteur a pour rôle de protéger le système d'injection contre les flammes de combustion.According to the invention, the deflector 10 has an annular flange 14 which extends radially inwards (that is to say towards the X-X axis of the opening 6 of the chamber bottom). As explained later, this flange 14 of the baffle has the role of protecting the injection system against combustion flames.

Chaque système d'injection 8 possède un axe de révolution Y-Y et se compose notamment d'un injecteur de carburant solidaire du carter de turbomachine (non représenté sur les figures). La tête 16 de l'injecteur est disposée du côté amont 4a du fond de chambre 4 et elle est centrée sur l'axe Y-Y du système d'injection par l'intermédiaire d'une bague de centrage 18 qui l'entoure.Each injection system 8 has an axis of revolution Y-Y and consists in particular of a fuel injector integral with the turbomachine casing (not shown in the figures). The head 16 of the injector is disposed on the upstream side 4a of the chamber bottom 4 and is centered on the Y-Y axis of the injection system via a centering ring 18 which surrounds it.

Une ou plusieurs vrilles d'air 20 éventuellement munies d'un venturi 22 sont fixées à l'extrémité aval de la bague de centrage 18 du système d'injection. Ce ou ces vrilles d'air 20 permettent à de l'air de pénétrer dans le système d'injection selon une direction essentiellement radiale et de se mélanger au carburant délivré par la tête 16 de l'injecteur de carburant. Le mélange air/carburant pénètre alors dans la chambre de combustion 2 pour y être enflammé.One or more air swivels 20 optionally provided with a venturi 22 are attached to the downstream end of the centering ring 18 of the injection system. This or these air swirlers 20 allow air to enter the injection system in a substantially radial direction and to mix with the fuel delivered by the head 16 of the fuel injector. The air / fuel mixture then enters the combustion chamber 2 to be ignited.

Chaque système d'injection 8 comporte également une bague 24 dite de pincement qui est montée du côté amont 4a du fond de chambre 4 et fixée contre le fourreau 12 de maintien du déflecteur 10. Cette bague de pincement 24 est centrée sur l'axe X-X de l'ouverture 6 du fond de chambre et définit avec le fourreau 12 une rainure annulaire 26 qui est ouverte du côté de l'axe X-X.Each injection system 8 also comprises a so-called pinch ring 24 which is mounted on the upstream side 4a of the chamber bottom 4 and fixed against the sleeve 12 for holding the deflector 10. This pinch ring 24 is centered on the axis XX of the opening 6 of the chamber bottom and defines with the sleeve 12 an annular groove 26 which is open on the side of the axis XX.

Chaque système d'injection 8 comporte encore un bol 28 fixé contre l'extrémité aval de la vrille d'air 20 et dont la fonction est d'assurer une bonne répartition du mélange air/carburant dans la zone primaire du foyer de combustion.Each injection system 8 further comprises a bowl 28 fixed against the downstream end of the air swirler 20 and whose function is to ensure a good distribution of the air / fuel mixture in the primary zone of the combustion chamber.

Le bol 28 est monté dans l'ouverture 6 correspondante du fond de chambre 4 et traverse celle-ci. Il se présente sous une forme générale d'un anneau centré sur l'axe Y-Y du système d'injection et se termine à son extrémité aval par une gorge annulaire 30 à section en U qui est ouverte vers l'extérieur (c'est-à-dire du côté opposé à l'axe X-X de l'ouverture du fond de chambre) et alignée radialement avec la collerette 14 du déflecteur 10.The bowl 28 is mounted in the corresponding opening 6 of the chamber bottom 4 and passes therethrough. It is generally in the form of a ring centered on the YY axis of the injection system and terminates at its downstream end by a U-shaped annular groove 30 which is open towards the outside (ie that is to say on the opposite side to the axis XX of the opening of the chamber bottom) and radially aligned with the flange 14 of the deflector 10.

A son extrémité amont, le bol 28 comporte un flasque annulaire 32 monté du côté amont 4a du fond de chambre 4 et apte à coulisser radialement à l'intérieur de la rainure 26 formée entre la bague de pincement 24 et le fourreau 12 de maintien du déflecteur 10 de façon à autoriser un décentrage du système d'injection 8 par rapport au fond de chambre 4.At its upstream end, the bowl 28 comprises an annular flange 32 mounted on the upstream side 4a of the chamber bottom 4 and able to slide radially inside the groove 26 formed between the clamping ring 24 and the sleeve 12 for holding the deflector 10 so as to allow an off-centering of the injection system 8 with respect to the chamber bottom 4.

Ainsi, la tête 16 de l'injecteur de carburant et l'ensemble du système d'injection 8 sont montés coulissant par rapport au fond de chambre 4 afin de rattraper les écarts de dilatation thermique entre le carter et la chambre de combustion. Avec ce type d'agencement, la tête 16 de l'injecteur de carburant reste donc en permanence centrée par rapport au système d'injection 8.Thus, the head 16 of the fuel injector and the entire injection system 8 are slidably mounted relative to the chamber bottom 4 in order to make up for the thermal expansion gaps between the casing and the combustion chamber. With this type of arrangement, the head 16 of the fuel injector therefore remains permanently centered with respect to the injection system 8.

Le flasque 32 du bol se prolonge vers l'aval par une partie 34 sensiblement cylindrique de diamètre inférieur à celui de l'ouverture 6 et qui se raccorde à la gorge 30 par un épaulement annulaire 36 du côté amont de celle-ci. La gorge 30 est disposée derrière une bride annulaire 38 qui s'étend radialement vers l'extérieur et dont le diamètre est inférieur à celui de l'épaulement 36.The flange 32 of the bowl is extended downstream by a substantially cylindrical portion 34 of smaller diameter than that of the opening 6 and which is connected to the groove 30 by an annular shoulder 36 on the upstream side thereof. The groove 30 is disposed behind an annular flange 38 which extends radially outwards and whose diameter is smaller than that of the shoulder 36.

La gorge 30 du bol est formée de deux parois latérales annulaires qui sont espacées axialement et reliées à leur extrémité intérieure par un fond annulaire 40, l'une de ces parois 42 étant reliée à son extrémité extérieure à l'épaulement 36 et l'autre paroi 44 étant reliée à son extrémité extérieure à la bride 38.The groove 30 of the bowl is formed of two annular lateral walls which are spaced axially and connected at their inner end by an annular bottom 40, one of these walls 42 being connected at its outer end to the shoulder 36 and the other wall 44 being connected at its outer end to the flange 38.

La bride 38 est la partie du bol qui est située le plus en aval. Cette bride se prolonge vers l'amont par une partie 46 qui est évasée vers l'aval, cette partie évasée 46 se prolongeant elle-même vers l'amont par une partie cylindrique 48 qui est concentrique à la partie cylindrique 34 du bol (et de diamètre inférieur à celle-ci) et se raccorde à la vrille d'air 20. La partie évasée 46 du bol est percée d'une pluralité de trous d'introduction d'air 50.The flange 38 is the part of the bowl which is located furthest downstream. This flange is extended upstream by a portion 46 which is flared downstream, this flared portion 46 extending itself upstream by a cylindrical portion 48 which is concentric with the cylindrical portion 34 of the bowl (and of smaller diameter than this) and is connected to the air swirler 20. The flared portion 46 of the bowl is pierced with a plurality of air introduction holes 50.

L'épaulement 36 du bol est également percé d'une pluralité de trous de ventilation 52 s'ouvrant du côté amont du fond de chambre 4 et débouchant du côté aval de celui-ci en regard de la collerette 14 du déflecteur 10. L'air circulant au travers de ces trous de ventilation 52 vient refroidir par l'amont la collerette 14 du déflecteur, puis circule dans la gorge 30 du bol afin de créer un film d'air circulant ensuite radialement le long du côté aval du déflecteur 10 afin de refroidir ce dernier.The shoulder 36 of the bowl is also pierced with a plurality of ventilation holes 52 opening on the upstream side of the chamber bottom 4 and opening on the downstream side thereof facing the collar 14 of the deflector 10. The air flowing through these ventilation holes 52 is cooled by the upstream flange 14 of the baffle, then flows into the groove 30 of the bowl to create a film of air flowing thereafter radially along the downstream side of the deflector 10 so to cool the latter.

On décrira maintenant le fonctionnement d'un tel agencement notamment en cas de décentrage du système d'injection 8 par rapport au fond de chambre 4.The operation of such an arrangement will now be described, in particular in the case of off-centering of the injection system 8 with respect to the chamber bottom 4.

Sur la figure 1, il n'y a aucun décentrage entre le système d'injection 8 par rapport au fond de chambre 4 (l'axe X-X de l'ouverture 6 du fond de chambre est aligné avec l'axe de révolution Y-Y du système d'injection). Dans cette situation, la collerette 14 du déflecteur 10 qui s'étend radialement vers l'intérieur assure bien une protection thermique efficace du système d'injection (et notamment du flasque 32) contre les flammes de combustion.On the figure 1 there is no decentering between the injection system 8 with respect to the chamber bottom 4 (the axis XX of the opening 6 of the chamber bottom is aligned with the axis of revolution YY of the injection system ). In this situation, the flange 14 of the deflector 10 which extends radially inwardly ensures effective thermal protection of the injection system (and in particular the flange 32) against the combustion flames.

La figure 2 représente l'un des deux cas possibles de décentrage maximum entre le système d'injection et le fond de chambre (l'axe de révolution Y-Y du système d'injection est décalé radialement vers l'extérieur par rapport à l'axe X-X de l'ouverture du fond de chambre). Dans cette situation, la distance radiale séparant l'épaulement 36 du fond 40 de la gorge 30 du bol est de préférence au moins égale à la hauteur radiale de la collerette 14 du déflecteur 10 de sorte que cette collerette peut se rétracter entièrement dans la gorge du bol. Le flasque 32 du système d'injection qui est complètement rétracté dans la rainure 26 est ainsi bien protégé contre les flammes de combustion.The figure 2 represents one of the two possible cases of maximum decentering between the injection system and the chamber bottom (the axis of revolution YY of the injection system is shifted radially outwards with respect to the axis XX of the opening of the chamber floor). In this situation, the radial distance separating the shoulder 36 from the bottom 40 of the groove 30 of the bowl is preferably at least equal to the radial height of the flange 14 of the baffle 10 so that this flange can fully retract into the throat of the bowl. The flange 32 of the injection system which is completely retracted into the groove 26 is thus well protected against combustion flames.

La figure 3 représente l'autre cas possible de décentrage maximum entre le système d'injection et le fond de chambre (l'axe de révolution Y-Y du système d'injection est décalé radialement vers l'intérieur par rapport à l'axe X-X de l'ouverture du fond de chambre). Dans cette situation, la collerette 14 du déflecteur 10 continue d'assurer son rôle de protection thermique du système d'injection contre les flammes de combustion en couvrant entièrement le flasque 32. Ceci est du au fait que la hauteur radiale de la collerette 14 du déflecteur est de préférence au moins égale à celle du flasque 32 du bol.The figure 3 represents the other possible case of maximum decentering between the injection system and the chamber bottom (the axis of revolution YY of the injection system is shifted radially inwards with respect to the axis XX of the opening from the bedroom floor). In this situation, the flange 14 of the baffle 10 continues to perform its role of thermal protection of the injection system against combustion flames by completely covering the flange 32. This is due to the fact that the radial height of the flange 14 of the flange deflector is preferably at least equal to that of the flange 32 of the bowl.

Selon une caractéristique avantageuse de l'invention, la distance séparant les parois latérales 42, 44 de la gorge 30 du bol est supérieure à l'épaisseur de la collerette 14 du déflecteur 10 de façon à autoriser une circulation de l'air de ventilation traversant les trous 52 percés dans l'épaulement 36 quelque soit le décentrage du système d'injection par rapport au fond de chambre. Ainsi, dans le cas extrême de décentrage de la figure 2, l'air de ventilation empruntant les trous 52 continue de circuler à l'intérieur de la gorge 30 en contournant la collerette 14 du déflecteur.According to an advantageous characteristic of the invention, the distance separating the lateral walls 42, 44 of the groove 30 of the bowl is greater than the thickness of the collar 14 of the deflector 10 so as to allow a circulation of the ventilation air passing through the holes 52 drilled in the shoulder 36 whatever the decentering of the injection system relative to the chamber bottom. So, in the extreme case of decentering the figure 2 , the ventilation air passing through the holes 52 continues to circulate inside the groove 30 bypassing the flange 14 of the baffle.

Le montage de l'agencement selon l'invention s'effectue de la manière suivante. Le fourreau 12 de maintien du déflecteur, le bol 28, la bague de pincement 24, la vrille d'air 20 et la bague de centrage 18 sont montés par l'amont (c'est-à-dire par le côté amont 4a du fond de chambre 4) et fixés les uns aux autres (par brasure ou par soudure par exemple). Le déflecteur 10 est quant à lui monté dans l'ouverture 6 du fond de chambre 4 par l'aval (c'est-à-dire par le côté aval 4b du fond de chambre) puis fixé au fourreau 12.The assembly of the arrangement according to the invention is carried out as follows. The sleeve 12 for holding the deflector, the bowl 28, the clamping ring 24, the air swirler 20 and the centering ring 18 are mounted upstream (that is to say by the upstream side 4a of the chamber bottom 4) and fixed to each other (soldered or welded for example). The deflector 10 is mounted in the opening 6 of the chamber bottom 4 downstream (that is to say by the downstream side 4b of the chamber bottom) and then fixed to the sheath 12.

On comprend ainsi que, même en cas de rupture de la brasure ou de la soudure de liaison entre les différentes pièces constitutives du système d'injection, aucune d'entre elles ne peut pas tomber dans la chambre de combustion 2.It is thus understood that, even in the event of breakage of the solder or the connection weld between the various constituent parts of the injection system, none of them can fall into the combustion chamber 2.

On comprend également que compte tenu que le déflecteur 10 est monté par l'aval, la collerette 14 de celui-ci peut présenter un diamètre inférieur à celui de l'ouverture 6 du fond de chambre 4 qui est choisi en fonction des écarts maximums de décentrage possible du système d'injection par rapport au fond de chambre afin d'assurer en permanence une protection thermique du système d'injection contre les flammes de combustion.It is also understood that since the deflector 10 is mounted downstream, the flange 14 thereof may have a smaller diameter than the opening 6 of the chamber bottom 4 which is chosen according to the maximum deviations of possible decentering of the system injection in relation to the chamber bottom so as to permanently ensure thermal protection of the injection system against the combustion flames.

Claims (9)

  1. An arrangement for a turbomachine combustion chamber, comprising a chamber end wall (4) pierced by at least one substantially circular opening (6), a deflector (10) mounted from the downstream side (4b) of the chamber end wall in the opening (6) by means of an annulus (12), an injector system (8) associated with the opening and including an annular bowl (28) that is flared downstream, passing through said opening, the bowl (28) of the injector system including at its downstream end an outwardly-open annular groove (30), and means enabling the injector system to shift off-center relative to the chamber end wall, the arrangement being characterized in that the deflector (10) includes an annular collar (14) extending radially inwards, and in that the annular groove (30) is radially in alignment with the collar (14) of the deflector in such a manner as to enable it to retract into said groove in the event of the injector system shifting off-center relative to the chamber end wall.
  2. An arrangement according to claim 1, in which the annular groove (30) of the bowl is formed by two side walls (42, 44) that are axially spaced apart and interconnected by an annular bottom wall (40), the distance between said side walls (42, 44) of the groove being greater than the thickness of the collar (14) of the deflector (10) so as to allow ventilation air to flow regardless of the off-centering of the injector system relative to the chamber end wall.
  3. An arrangement according to claim 1 or claim 2, in which the means enabling the injector system to shift off-center relative to the chamber end wall comprise a pinch ring (24) mounted from the upstream side (4a) of the chamber end wall (4) and fastened against the annulus (12) whereby together they define an annular groove (36) that is open towards the axis (X-X) of the opening (6) in the chamber end wall, the bowl (28) of the injector system further including an annular end plate (32) suitable for sliding radially in the groove (26) formed by the pinch ring and the annulus.
  4. An arrangement according to claim 3, in which the end plate (32) of the bowl (28) is extended downstream by a substantially cylindrical portion (34) that is connected to the groove (30) by an annular shoulder (36).
  5. An arrangement according to claim 4, in which the shoulder (36) of the bowl (28) is pierced by a plurality of ventilation holes (52) open to the upstream side (4a) of the chamber end wall and leading to the downstream side (4b) thereof in register with the collar (14) of the deflector (10).
  6. An arrangement according to any one of claims 3 to 5, in which the radial height of the collar (14) of the deflector (10) is not less than that of the end plate (32) of the bowl (28) so as to protect the injector system regardless of the extent to which the injector system is off-center relative to the chamber end wall.
  7. An arrangement according to any one of claims 1 to 6, in which the injector system (8) further includes at least one air swirler (20) fastened to the upstream end of the bowl (28), and a centering ring (18) fastened to the upstream end of the air swirler and surrounding a fuel injector (16).
  8. A turbomachine combustion chamber including an arrangement according to any one of claims 1 to 7.
  9. A turbomachine including an arrangement according to any one of claims 1 to 7.
EP07110586A 2006-06-29 2007-06-19 Arrangement for a gas turbine combustion chamber having a deflector with flange Active EP1873458B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0652718A FR2903172B1 (en) 2006-06-29 2006-06-29 ARRANGEMENT FOR A TURBOMACHINE COMBUSTION CHAMBER HAVING A FLANGE FAULT

Publications (2)

Publication Number Publication Date
EP1873458A1 EP1873458A1 (en) 2008-01-02
EP1873458B1 true EP1873458B1 (en) 2011-08-10

Family

ID=37714457

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07110586A Active EP1873458B1 (en) 2006-06-29 2007-06-19 Arrangement for a gas turbine combustion chamber having a deflector with flange

Country Status (5)

Country Link
US (1) US7823392B2 (en)
EP (1) EP1873458B1 (en)
CA (1) CA2592626C (en)
FR (1) FR2903172B1 (en)
RU (1) RU2435105C2 (en)

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7628019B2 (en) * 2005-03-21 2009-12-08 United Technologies Corporation Fuel injector bearing plate assembly and swirler assembly
FR2920525B1 (en) * 2007-08-31 2014-06-13 Snecma SEPARATOR FOR SUPPLYING THE COOLING AIR OF A TURBINE
US9127842B2 (en) 2009-05-27 2015-09-08 Siemens Aktiengesellschaft Burner, operating method and assembly method
FR2952166B1 (en) * 2009-11-05 2012-01-06 Snecma FUEL MIXER DEVICE FOR TURBOMACHINE COMBUSTION CHAMBER COMPRISING IMPROVED AIR SUPPLY MEANS
FR2964177B1 (en) * 2010-08-27 2012-08-24 Snecma AIRCRAFT ENGINE COMBUSTION CHAMBER AND METHOD OF FIXING AN INJECTION SYSTEM IN AN AIRCRAFT ENGINE COMBUSTION CHAMBER
US20120137691A1 (en) * 2010-12-01 2012-06-07 Bottcher Andreas Gas turbine assembly and method therefor
US9488105B2 (en) 2010-12-01 2016-11-08 Siemens Aktiengesellschaft Gas turbine assembly and method therefor
FR2970551B1 (en) * 2011-01-14 2017-12-22 Snecma DETACHABLE INJECTOR NOSE FOR AIRCRAFT TURBINE ENGINE COMBUSTION ROOM FUEL INJECTOR
FR2986856B1 (en) * 2012-02-15 2018-05-04 Safran Aircraft Engines DEVICE FOR INJECTING AIR AND FUEL FOR A COMBUSTION CHAMBER OF A TURBOMACHINE
FR2987428A1 (en) * 2012-02-23 2013-08-30 Snecma Arrangement for combustion chamber of e.g. turbopropeller of aircraft, has ring system including interior track having complementary form to that of outer surface, where track cooperates with outer surface to form connection kneecap
EP2831508A1 (en) * 2012-03-29 2015-02-04 ALSTOM Technology Ltd Gas turbine combustor
GB201321193D0 (en) * 2013-12-02 2014-01-15 Rolls Royce Plc A combustion chamber assembly
GB2543803B (en) * 2015-10-29 2019-10-30 Rolls Royce Plc A combustion chamber assembly
RU2677914C1 (en) * 2018-04-10 2019-01-22 Анатолий Иванович Софронов Internal combustion turbo engine
FR3082284B1 (en) * 2018-06-07 2020-12-11 Safran Aircraft Engines COMBUSTION CHAMBER FOR A TURBOMACHINE
FR3083264B1 (en) * 2018-06-29 2021-06-18 Safran Aircraft Engines GUIDANCE DEVICE IN A COMBUSTION CHAMBER
FR3103540B1 (en) * 2019-11-26 2022-01-28 Safran Aircraft Engines Fuel injection system of a turbomachine, combustion chamber comprising such a system and associated turbomachine

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4454711A (en) * 1981-10-29 1984-06-19 Avco Corporation Self-aligning fuel nozzle assembly
US4606190A (en) * 1982-07-22 1986-08-19 United Technologies Corporation Variable area inlet guide vanes
FR2639095B1 (en) * 1988-11-17 1990-12-21 Snecma COMBUSTION CHAMBER OF A TURBOMACHINE WITH FLOATING MOUNTS PREVAPORIZATION BOWLS
FR2679010B1 (en) * 1991-07-10 1993-09-24 Snecma TURBOMACHINE COMBUSTION CHAMBER WITH REMOVABLE PREVAPORIZATION BOWLS.
DE19508111A1 (en) * 1995-03-08 1996-09-12 Bmw Rolls Royce Gmbh Heat shield arrangement for a gas turbine combustor
FR2753779B1 (en) * 1996-09-26 1998-10-16 AERODYNAMIC INJECTION SYSTEM FOR A FUEL AIR MIXTURE
US6530227B1 (en) * 2001-04-27 2003-03-11 General Electric Co. Methods and apparatus for cooling gas turbine engine combustors
FR2825778A1 (en) * 2001-06-06 2002-12-13 Snecma Moteurs Coupling between fuel injector nozzle and turbine combustion chamber base has metal mixer/deflector assembly sliding in composition base aperture
FR2832493B1 (en) * 2001-11-21 2004-07-09 Snecma Moteurs MULTI-STAGE INJECTION SYSTEM OF AN AIR / FUEL MIXTURE IN A TURBOMACHINE COMBUSTION CHAMBER
US6871501B2 (en) * 2002-12-03 2005-03-29 General Electric Company Method and apparatus to decrease gas turbine engine combustor emissions
US7140189B2 (en) * 2004-08-24 2006-11-28 Pratt & Whitney Canada Corp. Gas turbine floating collar
FR2886714B1 (en) * 2005-06-07 2007-09-07 Snecma Moteurs Sa ANTI-ROTARY INJECTION SYSTEM FOR TURBO-REACTOR
FR2903169B1 (en) * 2006-06-29 2011-11-11 Snecma DEVICE FOR INJECTING A MIXTURE OF AIR AND FUEL, COMBUSTION CHAMBER AND TURBOMACHINE HAVING SUCH A DEVICE
FR2903171B1 (en) * 2006-06-29 2008-10-17 Snecma Sa CRABOT LINK ARRANGEMENT FOR TURBOMACHINE COMBUSTION CHAMBER

Also Published As

Publication number Publication date
FR2903172B1 (en) 2008-10-17
US7823392B2 (en) 2010-11-02
CA2592626C (en) 2014-04-08
CA2592626A1 (en) 2007-12-29
RU2007124389A (en) 2009-01-10
EP1873458A1 (en) 2008-01-02
FR2903172A1 (en) 2008-01-04
RU2435105C2 (en) 2011-11-27
US20080000447A1 (en) 2008-01-03

Similar Documents

Publication Publication Date Title
EP1873458B1 (en) Arrangement for a gas turbine combustion chamber having a deflector with flange
EP1873454B1 (en) Arrangement with bayonet-type connection for gas turbine combustion chamber
EP1826492B1 (en) Arrangement for a combustion chamber of a turbine engine
EP2501996B1 (en) Combustion chamber having a ventilated spark plug
EP1793168A1 (en) Device for the injection of mixture of fuel and air, turbomachine and combustor with such a device
EP1873455A1 (en) Device for injecting a mix of air and fuel, combustion chamber and turbomachine equipped with such a device
CA2636923A1 (en) Optimization of an anti-coking film in an injection system
EP3569929B1 (en) Assembly for a turbine engine combustion chamber
EP2071242A1 (en) Device for injecting a mixture of air and fuel into a combustion chamber of a turbomachine
CA2862410A1 (en) Air and fuel injection device for a turbomachine combustion chamber
EP1058052B1 (en) Liquid fuel burner with low NOx and dust emission and atomizer therefor
EP2037174B1 (en) Handtool with improved gas combustion
EP0967434B1 (en) Burner with concentric air ducts and central stabilizer
FR2910115A1 (en) DEFLECTOR FOR BOTTOM OF COMBUSTION CHAMBER, COMBUSTION CHAMBER BEING EQUIPPED AND TURBOREACTOR COMPRISING THE SAME
FR2909437A1 (en) Rectilinear radial flame-holder device i.e. flame-holder arm for turbojet engine, has shell/cover and fuel injecting tube extended in gutter, where device is arranged such that fuel is injected in gas stream through wall of gutter
CA2152397A1 (en) Gas torch nozzle
FR2570473A1 (en) Improvements to gas boilers with parallel flow comprising a rose and a flame retention baffle (hub) relating to gas boilers and independent supply of combustion air
EP4179256B1 (en) Annular combustion chamber for an aircraft turbomachine
EP1980788B1 (en) Gaseous fuel burner
EP2017529A1 (en) Burner
WO2021209711A1 (en) Spark plug for a single-piece combustion chamber
FR3070751A1 (en) COMBUSTION CHAMBER HAVING AN IMPROVED DISTRIBUTION OF COOLING HOLES
FR2989451A1 (en) Deflector for injection system of combustion chamber of e.g. turbojet of aircraft, has annular shoulder intended to abut against bottom of chamber of injection system, and equipped with recesses spaced angularly from each other
EP0162761A1 (en) Burner with vanes and a well-balanced secondary air supply

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20070619

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

AKX Designation fees paid

Designated state(s): DE FR GB IT

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB IT

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602007016378

Country of ref document: DE

Effective date: 20111006

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20120511

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602007016378

Country of ref document: DE

Effective date: 20120511

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 10

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 11

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES, FR

Effective date: 20170719

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 12

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20230523

Year of fee payment: 17

Ref country code: FR

Payment date: 20230523

Year of fee payment: 17

Ref country code: DE

Payment date: 20230523

Year of fee payment: 17

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20230523

Year of fee payment: 17