EP0251895A1 - Annular gas turbine combustor having a controlling device for the primary air - Google Patents

Annular gas turbine combustor having a controlling device for the primary air Download PDF

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Publication number
EP0251895A1
EP0251895A1 EP87401444A EP87401444A EP0251895A1 EP 0251895 A1 EP0251895 A1 EP 0251895A1 EP 87401444 A EP87401444 A EP 87401444A EP 87401444 A EP87401444 A EP 87401444A EP 0251895 A1 EP0251895 A1 EP 0251895A1
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EP
European Patent Office
Prior art keywords
cap
combustion chamber
chamber
external
rotation
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP87401444A
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German (de)
French (fr)
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EP0251895B1 (en
Inventor
Gérard Marcel François Mandet
Rodolphe Martinez
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Safran Aircraft Engines SAS
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Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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Publication of EP0251895B1 publication Critical patent/EP0251895B1/en
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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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/26—Controlling the air flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2250/00—Geometry
    • F05B2250/40—Movement of component
    • F05B2250/41—Movement of component with one degree of freedom
    • F05B2250/411—Movement of component with one degree of freedom in rotation

Definitions

  • the present invention relates to annular combustion chambers, in particular for turbomachines comprising so-called variable geometry injectors.
  • One solution consists in continuously adapting, depending on the engine speed, the distribution of the air flow intended to form the fuel-air fuel mixture by means of movable shutters capable of diaphragm glus or less the air inlets associated with the injectors.
  • This type of control means poses two problems, one relating to the existence of as many rods, forks and other levers, in the vein, as there are injectors thus disturbing the flow of the cooling gases of the external wall of the chamber, the other problem coming from the large number of control devices passing through the casing and the sealing of which must be ensured in an identical and multiplied manner.
  • the synchronization of the diaphragms is carried out by a ring positioned between the chamber casing and the external wall of the chamber and connecting the levers of the various diaphragms.
  • This type of ring also has the drawback of disturbing the flow of cooling gases from the external wall and of preventing the production of a regular cooling wall film.
  • each diaphragm control lever passes through the cylindrical surface of the chamber and the roller bearing, which in turn makes the realization somewhat illusory, on the other hand due to a very poor guiding of the cooling air on the external wall of the chamber and towards the external swirl of the injector and by the presence of a cavity annular formed by the cylindrical bearing surface carrying the control ring, this cavity forming a dead end around the injector and creating uncontrolled turbulence which disturbs the guiding of the air towards the spin.
  • the object of the present invention is to improve control devices for this type of combustion chamber with variable geometry injectors by eliminating the control rings arranged in the vein between the chamber casing and the external wall of the chamber and avoiding also the control rings external to the casing, while ensuring optimal synchronization of rotation of all the diaphragms.
  • the invention also aims to allow this control of the diaphragms on a combustion chamber comprising on its outer wall a rounded circular ferrule, called a cap, ensuring the guiding of the air on the one hand towards the injection devices and on the other hand towards the external wall to produce a parietal film, without disturbing said cooling film.
  • the invention therefore relates to an annular combustion chamber, in particular for turbomachines comprising a series of air and fuel injectors with axes parallel to the longitudinal axis of symmetry of the chamber, regularly distributed in a crown on the bottom chamber, each injector having an external swirl swirl intended for the introduction into the injection device of a first fraction of air to form a fuel air-fuel mixture.
  • the external turbulence tendrils are formed of fins defining channels which can be closed by a movable diaphragm in rotation around the injector, the combustion chamber comprises on the radially external part of its chamber bottom a cap with quarter-round section oriented downstream, said cap being capable of guiding the first fraction of the compressed air in the vein towards the injection device and a second fraction of said compressed air towards the external wall of the combustion chamber to ensure cooling by external convection.
  • the cap is made to rotate about the longitudinal axis of symmetry of the combustion chamber under the action of a first control means and comprises second means for simultaneously driving each diaphragm in rotation by the external turbulence spin of each injector around the axis of the latter.
  • the second means for simultaneously driving all the diaphragms in rotation are constituted by lugs regularly distributed over the upstream part of the cap, the number of lugs being equal to that of the diaphragms whose rotation movement must be controlled, each lug cooperating with a fork carried by the diaphragm which it controls.
  • a rotary bearing means can be interposed between the cap and the external wall of the combustion chamber, this means possibly being, according to a preferred embodiment, constituted by a ball ring in rolling contact on a first biconical circular track of the inner part of the cap and on a second circular track of the outer wall of the chamber, or according to a second embodiment, by a ring made of anti-friction material.
  • annular combustion chamber for a turbomachine in particular for an aviation turbojet engine, is formed of an internal wall 1 and an external wall 2, each formed of several successive rings making between them an annular chamber of which the bottom chamber 3 receives a number of devices 4 for injecting air and fuel regularly distributed in a ring around its periphery.
  • the injection devices 4 will be described in more detail with reference to Figures 2 and following.
  • a ferrule 5 of quarter-round section here called a cap surmounts the chamber bottom 3 and the upstream part of the external wall 2 to distribute a first fraction F1 of the flow of compressed air coming from the compressor (located upstream of the chamber and not shown here) to the injection devices 4 and a second fraction F2 of the compressed air flow to the annular space between the outer wall 2 of the chamber and the chamber casing 6, this fraction F2 of the flow having for purpose on the one hand to ensure the external cooling of the walls of the chamber, and on the other hand to enter the chamber through mixing orifices 7 and dilution 8 to be mixed there with the fuel vaporized by the injection devices , mixture which will be burned and to bring the temperature of the air leaving the combustion chamber to a level compatible with the maximum temperature allowable by the high pressure turbine stages located downstream of the chamber and not shown here.
  • each injection device 4 comprises a central fuel injector 9, an internal spin 10 and an external turbulence spin 11, the two spins 10 and 11 cooperating with the injector 9 to deliver into the intermediate bowl 12 a sheet of sprayed fuel.
  • a diaphragm 13 makes it possible to continuously open or close the external spin 12 to adapt the air flow that it delivers to the engine speed.
  • the cap 5 is rotatably mounted on the upstream part of the external wall 2 by means of a ball ring formed by a cylindrical cage 14 pierced with round holes for housing the balls 15 and of which the downstream part 14a is curved outward to come into abutment against a step 16 of the cap 5 during assembly of the assembly, as will be seen later .
  • the balls 15 are in rolling contact on the one hand on a first circular biconical track 17 produced on the internal part of the cap 5 and on the other hand on a second biconical track produced by the cooperation of two parts: the upstream end frustoconical 2a of the external upstream shell 2 and a frustoconical bearing 18a of an internal ring 18 disposed internally at the shell upstream of the external wall 2.
  • the ring 18 comprises a single orifice 18b intended for the successive introduction of the balls 15 into the holes of the cage 14 and also comprises regularly distributed bores 18c intended to cooperate with bores 2b the ferrule 2 to allow the fixing of the internal ring on the ferrule by bolts 19.
  • the rotation of the cap 5 is obtained by a control device comprising a rotating shaft 20 mounted by means of a sealing gland 21 through the chamber casing, the shaft 20 bearing on its inside end of the housing, a fork 22 which is engaged with a single radial ball joint 23 carried by the cap 5.
  • the shaft 20 is rotated externally to the casing 6 by any known mechanical means (gear and rack system, link %), hydraulic (cylinder and link) or electrohydraulic controlled by the turbojet regulator.
  • the cap 5 rotates the diaphragms 13 of each injection device 4 by means of a threaded lug 21 cooperating with one end 21a, eccentric with respect to its thread, engaged in a fork 13a of the diaphragm 13.
  • the internal ring 18 is then placed under the ferrule 2 in the position in FIG. 3 where the orifice 18b for introducing the balls is released from the ferrule 2.
  • the cage 14 and then the cap 5 are put in place.
  • the balls 15 are then introduced one by one through the orifice 18b of the ring 18 and are positioned in the holes of the cage 14, the internal ring 18 being able to rotate freely thus makes it possible to compare the orifice 18b with each of the cage positioning holes 14.
  • the internal ring is then put in place by sliding under the ferrule 2 which then masks the orifice 18b until coincidence of the bores 2b and 18c, then secured for the bolts 19 whose screws are introduced through a notch 24 unique from the downstream edge of the cap 5 which can rotate freely.
  • the establishment of the ring 18 realizes the formation of the second biconical track formed of the frustoconical surfaces 2a, 18a forming the internal raceway of the balls 15, the cap 5 is pushed back towards the chamber bottom at the same time as the internal ring 18, which positions the ball ring on its two rolling tracks 17 and 2a, 18a.
  • the eccentric pins 21 can then be screwed into the bores 22, having first taken care to have engaged the locknuts 25, the ends 21a of the pins being positioned in the forks 13a of the diaphragms 13.
  • the diaphragms are adjusted by bringing all the injectors back to the full opening (or full closing) position (and the locknuts 25 can then be tightened to block the lugs, thus making it possible to synchronize the opening of all the injectors.
  • the fork 22 of the first means for controlling the rotation of the cap can be engaged on the ball 23 of the cap and then be secured to the shaft 20.
  • a sealing device for the bearing means formed by the ball ring or the ring 30 can be provided for example by adding internally to the cap 5 a radial ring 31 ( shown only in Figure 5) which will be (once the cap in position) upstream of the rolling means to prevent impurities (fatty substances, dust, etc.) from entering it.
  • the control device as provided by the present invention has the advantage of leaving in the vein a minimum number of parts since a single fork 22 and a single ball joint 23 allows the rotation of the cap which itself will cause around their respective axes the rotation of all the diaphragms simultaneously, the cap always fulfilling its function of guiding the air without the air flow being disturbed by additional elements introduced into the vein.
  • the device in its preferred mode of embodiment where the rolling contact is made by means of a ball ring is simple enough to function correctly in the whole temperature range of use of the combustion chamber by means of a suitable calculation of the clearances between the cap, the balls and the inner ring. These clearances will be made up thanks to the axial force exerted by the air on the cap and the biconical shape of the two rolling tracks. Thus in operation, the cap will remain self-centered with respect to the chamber while supporting the relative expansions without jamming.
  • the materials used can remain the same as on a conventional chamber, for example the superalloy known under the trade name "Hastelloy X" with possibly a hardening surface treatment on the conical tracks.
  • injectors of different types can be combined with the devices with intermediate bowls previously mentioned.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)

Abstract

L'invention concerne la commande d'injecteurs à géométrie variable pour chambre de combustion annulaire d'une turbomachine. Selon l'invention, la casquette (5) de guidage d'air entourant la paroi externe de la chambre est montée tournante au moyen d'une couronne à billes (14,15) sur la virole externe amont (2) de la chambre, sous l'action d'un moyen de commande (20,22,23) et comporte des seconds moyens (13a, 21) pour que sa rotation autour de l'axe du moteur entraine la rotation simultanée des diaphragmes (13) de tous les injecteurs à géométrie variable autour de leur axe propre. Application aux turboréacteurs d'aviation à faible niveau de pollution.The invention relates to the control of variable geometry injectors for an annular combustion chamber of a turbomachine. According to the invention, the cap (5) for guiding the air surrounding the outer wall of the chamber is rotatably mounted by means of a ball ring (14,15) on the upstream outer shroud (2) of the chamber, under the action of a control means (20,22,23) and comprises second means (13a, 21) so that its rotation around the axis of the motor causes the simultaneous rotation of the diaphragms (13) of all the injectors with variable geometry around their own axis. Application to aviation turbojets with low pollution level.

Description

La présente invention concerne les chambres de combustion annulaires, notamment pour turbomachines comportant des injecteurs dits à géométrie variable.The present invention relates to annular combustion chambers, in particular for turbomachines comprising so-called variable geometry injectors.

Les exigences en matière de prévention de la pollution et notamment la sévérité des normes édictées par les agences nationales de protection de l'environnement ont conduit les constructeurs de moteurs d'avions à rechercher des moyens propres à réduire les taux de polluant dans les gaz d'échappement des moteurs.The requirements in terms of pollution prevention and in particular the severity of the standards enacted by the national environmental protection agencies have led aircraft engine manufacturers to look for ways to reduce the levels of pollutant in the exhaust gases. engine exhaust.

Une solution consiste à adapter de façon continue en fonction du régime du moteur, la répartition du débit d'air destiné à former le mélange combustible air­carburant au moyen de volets mobiles capables de diaphra­gmer glus ou moins les entrées d'air associées aux injecteurs.One solution consists in continuously adapting, depending on the engine speed, the distribution of the air flow intended to form the fuel-air fuel mixture by means of movable shutters capable of diaphragm glus or less the air inlets associated with the injectors.

Le brevet français n° 2 572 463 au nom de la demanderesse montre un exemple de ces dispositifs d'injection à géométrie variable. Dans ce brevet, le diaphragme porté par la vrille de turbulence externe de chaque injecteur est actionné par un levier commandé par une fourchette portée par un axe tourillonant dans un bossage solidaire du carter de la chambre. Il existe donc autant de dispositifs de commande traversant le carter que de diaphragmes à commander, la synchronisation de mise en mouvement de tous les systèmes d'injection étant effectuée par un anneau de synchronisation externe au carter de la chambre.French Patent No. 2,572,463 in the name of the Applicant shows an example of these variable geometry injection devices. In this patent, the diaphragm carried by the external turbulence spin of each injector is actuated by a lever controlled by a fork carried by a swiveling axis in a boss secured to the housing of the chamber. There are therefore as many control devices passing through the casing as there are diaphragms to be controlled, the synchronization of setting in motion of all the injection systems being effected by a synchronization ring external to the casing of the bedroom.

Ce type de moyen de commande pose deux problèmes, l'un tenant à l'existence d'autant de biellettes, fourchettes et autres leviers, dans la veine, qu'il existe d'injecteurs perturbant ainsi l'écoulement des gaz de refroidissement de la paroi externe de la chambre, l'autre problème provenant du grand nombre de dispositifs de commande traversant le carter et dont l'étanchéité doit être assurée de façon identique et multipliée.This type of control means poses two problems, one relating to the existence of as many rods, forks and other levers, in the vein, as there are injectors thus disturbing the flow of the cooling gases of the external wall of the chamber, the other problem coming from the large number of control devices passing through the casing and the sealing of which must be ensured in an identical and multiplied manner.

Dans d'autres réalisations, la synchronisation des diaphragmes est réalisée par un anneau positionné entre le carter de chambre et la paroi externe de la chambre et reliant les leviers des différents diaphragmes. Ce type d'anneau présente également l'inconvénient de perturber l'écoulement des gaz de refroidissement de la paroi externe et d'empêcher la réalisation d'un film pariétal régulier de refroidissement.In other embodiments, the synchronization of the diaphragms is carried out by a ring positioned between the chamber casing and the external wall of the chamber and connecting the levers of the various diaphragms. This type of ring also has the drawback of disturbing the flow of cooling gases from the external wall and of preventing the production of a regular cooling wall film.

Dans la demande de brevet français n° 2 491 140 a été montré un dispositif de commande par anneau externe monté sur un roulement à rouleaux monté sur une portée cylindrique de la chambre de combustion.In French patent application No. 2,491,140, an external ring control device has been shown mounted on a roller bearing mounted on a cylindrical bearing surface of the combustion chamber.

Un tel dispositif, s'il a le mérite de la simplicité, présente néanmoins plusieurs inconvénients rédhibitoires d'une part en raison du fait que chaque levier de commande de diaphragme traverse la portée cylindrique de la chambre et le roulement à rouleaux, ce qui en rend la réalisation quelque peu illusoire, d'autre part en raison d'un très mauvais guidage de l'air de refroidissement sur la paroi externe de la chambre et vers la vrille de turbulence externe de l'injecteur et par la présence d'une cavité annulaire formée par la portée cylindrique portant l'anneau de commande, cette cavité formant un cul-de-sac autour de l'injecteur et créant des turbulences non contrôlées qui perturbent le guidage de l'air vers la vrille.Such a device, if it has the merit of simplicity, nevertheless has several crippling drawbacks on the one hand due to the fact that each diaphragm control lever passes through the cylindrical surface of the chamber and the roller bearing, which in turn makes the realization somewhat illusory, on the other hand due to a very poor guiding of the cooling air on the external wall of the chamber and towards the external swirl of the injector and by the presence of a cavity annular formed by the cylindrical bearing surface carrying the control ring, this cavity forming a dead end around the injector and creating uncontrolled turbulence which disturbs the guiding of the air towards the spin.

La présente invention a pour but d'améliorer des dispositifs de commande de ce genre de chambres de combustion à injecteurs à géométrie variable en supprimant les anneaux de commande disposés dans la veine entre le carter de chambre et la paroi externe de la chambre et en évitant également les anneaux de commande externes au carter, tout en assurant une synchronisation optimale de rotation de tous les diaphragmes.The object of the present invention is to improve control devices for this type of combustion chamber with variable geometry injectors by eliminating the control rings arranged in the vein between the chamber casing and the external wall of the chamber and avoiding also the control rings external to the casing, while ensuring optimal synchronization of rotation of all the diaphragms.

L'invention a également pour but de permettre cette commande des diaphragmes sur une chambre de combustion comportant sur sa paroi externe une virole circulaire arrondie, appelée casquette, assurant le guidage de l'air d'une part vers les dispositifs d'injection et d'autre part vers la paroi externe pour réaliser un film pariétal, sans perturber ledit film de refroidissement.The invention also aims to allow this control of the diaphragms on a combustion chamber comprising on its outer wall a rounded circular ferrule, called a cap, ensuring the guiding of the air on the one hand towards the injection devices and on the other hand towards the external wall to produce a parietal film, without disturbing said cooling film.

L'invention a donc pour objet une chambre de combustion annulaire, notamment pour turbomachines comportant une série d'injecteurs d'air et de carburant d'axes parallèles à l'axe de symétrie longitudinale de la chambre, régulièrement répartis en couronne sur le fond de chambre, chaque injecteur possédant une vrille de turbulence externe destinée à l'introduction dans le dispositif d'injection d'une première fraction d'air pour former un mélange combustible air-carburant. Les vrilles de turbulence externe sont formées d'ailettes définissant des canaux pouvant être obturés par un diaphragme mobile en rotation autour de l'injecteur, la chambre de combustion comporte sur la partie radialement externe de son fond de chambre une casquette à section en quart de rond orienté vers l'aval, ladite casquette étant apte à assurer le guidage de la première fraction de l'air comprimé dans la veine vers le dispositif d'injection et d'une seconde fraction dudit air comprimé vers la paroi externe de la chambre de combustion pour en assurer le refroidissement par convection externe.The invention therefore relates to an annular combustion chamber, in particular for turbomachines comprising a series of air and fuel injectors with axes parallel to the longitudinal axis of symmetry of the chamber, regularly distributed in a crown on the bottom chamber, each injector having an external swirl swirl intended for the introduction into the injection device of a first fraction of air to form a fuel air-fuel mixture. The external turbulence tendrils are formed of fins defining channels which can be closed by a movable diaphragm in rotation around the injector, the combustion chamber comprises on the radially external part of its chamber bottom a cap with quarter-round section oriented downstream, said cap being capable of guiding the first fraction of the compressed air in the vein towards the injection device and a second fraction of said compressed air towards the external wall of the combustion chamber to ensure cooling by external convection.

Selon l'invention, la casquette est rendue mobile en rotation autour de l'axe de symétrie longitudinale de la chambre de combustion sous l'action d'un premier moyen de commande et comporte des seconds moyens pour entrainer en rotation simultanément chaque diaphragme porté par la vrille de turbulence externe de chaque injecteur autour de l'axe de ce dernier.According to the invention, the cap is made to rotate about the longitudinal axis of symmetry of the combustion chamber under the action of a first control means and comprises second means for simultaneously driving each diaphragm in rotation by the external turbulence spin of each injector around the axis of the latter.

Selon une particularité les seconds moyens pour entrainer en rotation simultanément tous les diaphragmes sont constitués par des ergots régulièrement répartis sur la partie amont de la casquette, le nombre d'ergots étant égal à celui des diaphragmes dont le mouvement en rotation doit être commandé, chaque ergot coopérant avec une fourchette portée par le diaphragme qu'il commande.According to one particular feature, the second means for simultaneously driving all the diaphragms in rotation are constituted by lugs regularly distributed over the upstream part of the cap, the number of lugs being equal to that of the diaphragms whose rotation movement must be controlled, each lug cooperating with a fork carried by the diaphragm which it controls.

Un moyen de palier tournant peut être interposé entre la casquette et la paroi externe de la chambre de combustion, ce moyen pouvant être selon un mode préférentiel de réalisation, constitué par une couronne à billes en contact de roulement sur une première piste circulaire biconique de la partie intérieure de la casquette et sur une deuxième piste circulaire de la paroi externe de la chambre, ou selon un second mode de réalisation, par un anneau réalisé en matériau anti-friction.A rotary bearing means can be interposed between the cap and the external wall of the combustion chamber, this means possibly being, according to a preferred embodiment, constituted by a ball ring in rolling contact on a first biconical circular track of the inner part of the cap and on a second circular track of the outer wall of the chamber, or according to a second embodiment, by a ring made of anti-friction material.

D'autres particularités et des détails de réalisation seront montrés en regard des figures annexées parmi lesquelles :

  • - la figure 1 est une vue en coupe longitudinale d'une chambre de combustion annulaire pour turbomachine incorporant le dispositif de commande selon l'invention ;
  • - la figure 2 montre le mode préféré de réalisation du dispositif de commande selon l'invention, également en coupe longitudinale selon le détail A de la figure 1 ;
  • - la figure 3 est une vue identique à la figure 2, les diverses pièces du dispositif étant écartées, pour assurer le montage des billes dans la cage de la couronne à billes;
  • - la figure 4 est une vue partielle du diaphragme et de son ergot de commande selon IV-IV de la figure 2, l'injecteur de carburant n'étant pas représenté ;
  • - la figure 5 montre un second mode de réalisation dans lequel la couronne à billes a été remplacée par un anneau en matériau anti-friction.
Other particularities and construction details will be shown with reference to the appended figures among which:
  • - Figure 1 is a longitudinal sectional view of an annular combustion chamber for a turbomachine incorporating the control device according to the invention;
  • - Figure 2 shows the preferred embodiment of the control device according to the invention, also in longitudinal section according to detail A of Figure 1;
  • - Figure 3 is a view identical to Figure 2, the various parts of the device being separated, to ensure the mounting of the balls in the cage of the ball crown;
  • - Figure 4 is a partial view of the diaphragm and its control pin according to IV-IV of Figure 2, the fuel injector not being shown;
  • - Figure 5 shows a second embodiment in which the ball crown has been replaced by a ring made of anti-friction material.

En référence à la figure 1, une chambre de combustion annulaire pour turbomachine, notamment pour turboréacteur d'aviation est formée d'une paroi interne 1 et d'une paroi externe 2, chacune formée de plusieurs viroles successives réalisant entre elles une chambre annulaire dont le fond de chambre 3 reçoit un certain nombre de dispositifs 4 d'injection d'air et de carburant régulièrement répartis en couronne sur son pourtour. Les dispositifs d'injection 4 seront décrits plus en détail en référence aux figures 2 et suivantes.With reference to FIG. 1, an annular combustion chamber for a turbomachine, in particular for an aviation turbojet engine, is formed of an internal wall 1 and an external wall 2, each formed of several successive rings making between them an annular chamber of which the bottom chamber 3 receives a number of devices 4 for injecting air and fuel regularly distributed in a ring around its periphery. The injection devices 4 will be described in more detail with reference to Figures 2 and following.

Une virole 5 de section en quart de rond ici appelée casquette surmonte le fond de chambre 3 et la partie amont de la paroi externe 2 pour répartir une première fraction F1 du flux d'air comprimé provenant du compresseur (situé en amont de la chambre et non représenté ici) vers les dispositifs d'injection 4 et une second fraction F2 du flux d'air comprimé vers l'espace annulaire compris entre la paroi externe 2 de la chambre et le carter de chambre 6, cette fraction F2 du flux ayant pour but d'une part d'assurer le refroidissement externe des parois de la chambre, et d'autre part de pénétrer dans la chambre par des orifices de mélange 7 et de dilution 8 pour y être mélangé au carburant vaporisé par les dispositifs d'injection, mélange qui sera brûlé et pour ramener la température de l'air sortant de la chambre de combustion à un niveau compatible avec la température maximale admissible par les étages de turbine haute pression situés en aval de la chambre et non représentés ici.A ferrule 5 of quarter-round section here called a cap surmounts the chamber bottom 3 and the upstream part of the external wall 2 to distribute a first fraction F1 of the flow of compressed air coming from the compressor (located upstream of the chamber and not shown here) to the injection devices 4 and a second fraction F2 of the compressed air flow to the annular space between the outer wall 2 of the chamber and the chamber casing 6, this fraction F2 of the flow having for purpose on the one hand to ensure the external cooling of the walls of the chamber, and on the other hand to enter the chamber through mixing orifices 7 and dilution 8 to be mixed there with the fuel vaporized by the injection devices , mixture which will be burned and to bring the temperature of the air leaving the combustion chamber to a level compatible with the maximum temperature allowable by the high pressure turbine stages located downstream of the chamber and not shown here.

Si l'on se réfère maintenant à la figure 2, chaque dispositif d'injection 4 comprend un injecteur central de carburant 9, une vrille interne 10 et une vrille de turbulence externe 11, les deux vrilles 10 et 11 coopérant avec l'injecteur 9 pour délivrer dans le bol intermédiaire 12 une nappe de carburant pulvérisé. Un diaphragme 13 permet d'ouvrir ou de fermer en continu la vrille externe 12 pour adapter le débit d'air que celle-ci débite au régime du moteur.Referring now to FIG. 2, each injection device 4 comprises a central fuel injector 9, an internal spin 10 and an external turbulence spin 11, the two spins 10 and 11 cooperating with the injector 9 to deliver into the intermediate bowl 12 a sheet of sprayed fuel. A diaphragm 13 makes it possible to continuously open or close the external spin 12 to adapt the air flow that it delivers to the engine speed.

De tels dispositifs d'injections sont maintenant bien connus et ont déjà été décrits notamment dans la demande française 2 572 463 déjà citée.Such injection devices are now well known and have already been described in particular in French application 2,572,463 already cited.

Pour venir plus précisément à l'objet de l'invention, selon son mode de réalisation préféré, la casquette 5 est montée tournante sur la partie amont de la paroi externe 2 au moyen d'une couronne à billes formée d'une cage 14 cylindrique percée de trous ronds pour le logement des billes 15 et dont la partie aval 14a est recourbée vers l'extérieur pour venir en butée contre un redan 16 de la casquette 5 lors du montage de l'ensemble, ainsi qu'on le verra plus loin.To come more precisely to the object of the invention, according to its preferred embodiment, the cap 5 is rotatably mounted on the upstream part of the external wall 2 by means of a ball ring formed by a cylindrical cage 14 pierced with round holes for housing the balls 15 and of which the downstream part 14a is curved outward to come into abutment against a step 16 of the cap 5 during assembly of the assembly, as will be seen later .

Les billes 15 sont en contact de roulement d'une part sur une première piste circulaire 17 biconique réalisée sur la partie interne de la casquette 5 et d'autre part sur une seconde piste biconique réalisée par la coopération de deux pièces : l'extrémité amont tronconique 2a de la virole amont externe 2 et une portée tronconique 18a d'un anneau interne 18 disposé intérieurement à la virole amont de la paroi externe 2.The balls 15 are in rolling contact on the one hand on a first circular biconical track 17 produced on the internal part of the cap 5 and on the other hand on a second biconical track produced by the cooperation of two parts: the upstream end frustoconical 2a of the external upstream shell 2 and a frustoconical bearing 18a of an internal ring 18 disposed internally at the shell upstream of the external wall 2.

L'anneau 18 comporte un orifice 18b unique destiné à l'introduction successive des billes 15 dans les trous de la cage 14 et comporte également des perçages régulièrement répartis 18c destinés à coopérer avec des perçages 2b la virole 2 pour permettre la fixation de l'anneau interne sur la virole par des boulons 19.The ring 18 comprises a single orifice 18b intended for the successive introduction of the balls 15 into the holes of the cage 14 and also comprises regularly distributed bores 18c intended to cooperate with bores 2b the ferrule 2 to allow the fixing of the internal ring on the ferrule by bolts 19.

La rotation de la casquette 5 est obtenue par un dispositif de commande comprenant un arbre tournant 20 monté au moyen d'un presse-étoupe d'étanchéité 21 au travers du carter de chambre, l'arbre 20 portant sur son extrémité intérieure au carter une fourchette 22 qui est en prise avec une rotule radiale 23 unique portée par la casquette 5.The rotation of the cap 5 is obtained by a control device comprising a rotating shaft 20 mounted by means of a sealing gland 21 through the chamber casing, the shaft 20 bearing on its inside end of the housing, a fork 22 which is engaged with a single radial ball joint 23 carried by the cap 5.

L'arbre 20 est entrainé en rotation extérieurement au carter 6 par tout moyen connu mécanique (système à engrenage et crémaillère, biellette ...), hydraulique (vérin et biellette) ou électrohydraulique commandé par le dispositif de régulation du turboréacteur.The shaft 20 is rotated externally to the casing 6 by any known mechanical means (gear and rack system, link ...), hydraulic (cylinder and link) or electrohydraulic controlled by the turbojet regulator.

La casquette 5 entraine en rotation les diaphragmes 13 de chaque dispositif d'injection 4 au moyen d'un ergot fileté 21 coopérant par une extrémité 21a, excentrée par rapport à son filetage, engagée dans une fourchette 13a du diaphragme 13. Chaque ergot 21 est vissé dans un taraudage 22 de la partie radiale amont de la casquette et après positivement de son extrémité excentrée, fixant le réglage d'ouverture simultanée des diaphragmes, peut être bloqué en position par un contre-écrou 25 =

le montage d'un tel ensemble tournant est effectué de la façon suivante en regard de la figure 3 :

les injecteurs à géométrie variable 4 équipés de leur diaphragme 13 sont montés sur le fond de chambre de façon classique. On dispose alor l'anneau interne 18 sous la virole 2 dans la position de la figure 3 où l'orifice 18b d'introduction des billes est dégagé de la virole 2. On met en place la cage 14 puis la casquette 5.The cap 5 rotates the diaphragms 13 of each injection device 4 by means of a threaded lug 21 cooperating with one end 21a, eccentric with respect to its thread, engaged in a fork 13a of the diaphragm 13. Each lug 21 is screwed into a thread 22 of the upstream radial part of the cap and after positively of its eccentric end, fixing the simultaneous opening adjustment of the diaphragms, can be locked in position by a lock nut 25 =

the mounting of such a rotating assembly is carried out as follows with regard to FIG. 3:

the injectors with variable geometry 4 equipped with their diaphragm 13 are mounted on the chamber bottom in a conventional manner. The internal ring 18 is then placed under the ferrule 2 in the position in FIG. 3 where the orifice 18b for introducing the balls is released from the ferrule 2. The cage 14 and then the cap 5 are put in place.

Les billes 15 sont ensuite introduites une à une par l'orifice 18b de l'anneau 18 et sont positionnées dans les trous de la cage 14, l'anneau interne 18 pouvant tourner librement permet ainsi de mettre en regard l'orifice 18b avec chacun des trous de positionnement de la cage 14.The balls 15 are then introduced one by one through the orifice 18b of the ring 18 and are positioned in the holes of the cage 14, the internal ring 18 being able to rotate freely thus makes it possible to compare the orifice 18b with each of the cage positioning holes 14.

L'anneau interne est alors mis en place par glissement sous la virole 2 ce qui masque alors l'orifice 18b jusqu'à coïncidence des alésages 2b et 18c, puis solidarisé pour les boulons 19 dont les vis sont introduites au travers d'une échancrure 24 unique du bord aval de la casquette 5 qui peut tourner librement. La mise en place de l'anneau 18 réalise la formation de la seconde piste biconique formée des portées tronconiques 2a, 18a formant le chemin de roulement interne des billes 15, la casquette 5 est repoussée vers le fond de chambre en même temps que l'anneau interne 18, ce qui positionne la couronne à billes sur ses deux pistes de roulement 17 et 2a, 18a.The internal ring is then put in place by sliding under the ferrule 2 which then masks the orifice 18b until coincidence of the bores 2b and 18c, then secured for the bolts 19 whose screws are introduced through a notch 24 unique from the downstream edge of the cap 5 which can rotate freely. The establishment of the ring 18 realizes the formation of the second biconical track formed of the frustoconical surfaces 2a, 18a forming the internal raceway of the balls 15, the cap 5 is pushed back towards the chamber bottom at the same time as the internal ring 18, which positions the ball ring on its two rolling tracks 17 and 2a, 18a.

On peut alors visser les ergots excentriques 21 dans les alésages 22 en ayant pris soin au préalable d'avoir engagé les contre-écrous 25, les extrémités 21a des ergots étant positionnées dans les fourchettes 13a des diaphragmes 13.The eccentric pins 21 can then be screwed into the bores 22, having first taken care to have engaged the locknuts 25, the ends 21a of the pins being positioned in the forks 13a of the diaphragms 13.

Le réglage des diaphragmes s'effectue en ramenant tous les injecteurs en position pleine ouverture (ou pleine fermeture( et les contre-écrous 25 peuvent alors être serrés pour bloquer les ergots, permettant ainsi de synchroniser l'ouverture de tous les injecteurs.The diaphragms are adjusted by bringing all the injectors back to the full opening (or full closing) position (and the locknuts 25 can then be tightened to block the lugs, thus making it possible to synchronize the opening of all the injectors.

Enfin la fourchette 22 du premier moyen de commande de mise en rotation de la casquette peut être engagée sur la rotule 23 de la casquette puis être solidarisée à l'arbre 20.Finally, the fork 22 of the first means for controlling the rotation of the cap can be engaged on the ball 23 of the cap and then be secured to the shaft 20.

Selon une variante simplifiée d'exécution représentée à la figure 5, on peut remplacer la couronne à billes 14,15 par un anneau en matériau antifriction résistant à chaud. Un tel anneau 30 peut avoir une section carrée à coins biseautés. La seule modification à apporter au dispositif précédemment décrit consiste à supprimer de l'anneau 18, l'orifice 18b d'introduction de billes, qui ne se justifie plus.According to a simplified variant of execution shown in the Figure 5, we can replace the ball ring 14,15 by a ring of heat resistant anti-friction material. Such a ring 30 may have a square section with bevelled corners. The only modification to be made to the device described above consists in removing from the ring 18, the orifice 18b for introducing balls, which is no longer justified.

Le reste du dispositif est sans changement et la mise en place de l'anneau 30 et des autres pièces du dispositif de commande ne déduira de façon simple des explications précédemment données.The rest of the device is unchanged and the installation of the ring 30 and the other parts of the control device will not simply deduce from the explanations previously given.

Dans les deux modes de réalisation on peut prévoir un dispositif d'étanchéité du moyen de palier formé par la couronne à billes ou l'anneau 30. Une telle étanchéité peut être réalisée par exemple en ajoutant intérieurement à la casquette 5 une couronne radiale 31 (représentée seulement à la figure 5) qui se trouvera (une fois la casquette en position) en amont du moyen de roulement pour empêcher les impuretés (corps gras, poussières, etc..) d'y pénétrer.In the two embodiments, it is possible to provide a sealing device for the bearing means formed by the ball ring or the ring 30. Such sealing can be achieved for example by adding internally to the cap 5 a radial ring 31 ( shown only in Figure 5) which will be (once the cap in position) upstream of the rolling means to prevent impurities (fatty substances, dust, etc.) from entering it.

Le dispositif de commande tel que prévu par la présente invention présente l'avantage de laisser dans la veine un nombre minimum de pièces puisqu'une seule fourchette 22 et une seule rotule 23 permet la rotation de la casquette qui elle-même entrainera autour de leurs axes respectifs la rotation de tous les diaphragmes simultanément, la casquette remplissant toujours sa fonction de guidage de l'air sans que le flux d'air soit perturbé par des éléments supplémentaires introduits dans la veine.The control device as provided by the present invention has the advantage of leaving in the vein a minimum number of parts since a single fork 22 and a single ball joint 23 allows the rotation of the cap which itself will cause around their respective axes the rotation of all the diaphragms simultaneously, the cap always fulfilling its function of guiding the air without the air flow being disturbed by additional elements introduced into the vein.

De plus, le dispositif dans son mode préféré de réalisation où le contact de roulement s'effectue au moyen d'une couronne à billes est suffisamment simple pour fonctionner correctement dans toute la plage de températures d'utilisation de la chambre de combustion moyennant un calcul convenable des jeux entre la casquette, les billes et l'anneau interne. Ces jeux seront rattrapés grâce à l'effort axial exercé par l'air sur la casquette et à la forme biconique des deux pistes de roulement. Ainsi en fonctionnement, la casquette restera autocentrée par rapport à la chambre tout en supportant les dilatations relatives sans coincement.In addition, the device in its preferred mode of embodiment where the rolling contact is made by means of a ball ring is simple enough to function correctly in the whole temperature range of use of the combustion chamber by means of a suitable calculation of the clearances between the cap, the balls and the inner ring. These clearances will be made up thanks to the axial force exerted by the air on the cap and the biconical shape of the two rolling tracks. Thus in operation, the cap will remain self-centered with respect to the chamber while supporting the relative expansions without jamming.

Compte-tenu des efforts modérés exercés sur les billes (environ 300 daN pour l'ensemble de la casquette), les matériaux utilisés peuvent rester les mêmes que sur une chambre classique, par exemple le supéralliage connu sous la dénomination commerciale "Hastelloy X" avec éventuellement un traitement de surface durcissant sur les pistes coniques.Given the moderate forces exerted on the balls (around 300 daN for the whole cap), the materials used can remain the same as on a conventional chamber, for example the superalloy known under the trade name "Hastelloy X" with possibly a hardening surface treatment on the conical tracks.

Il est évident qu'un tel dispositif ne s'applique pas seulement aux dispositifs d'injection possédant le bol particulier représenté sur les figures annexées, mais qu'il peut s'appliquer aussi aux dispositifs à bols sectorisés ou à bol élargi, le seul critère d'application étant la nécessité de commander un diaphragme de vrilles sur des dispositifs d'injection à géométrie variable disposés en couronne sur le fond d'une chambre de combustion annulaire.It is obvious that such a device does not only apply to injection devices having the particular bowl shown in the appended figures, but that it can also apply to devices with sectorized bowls or with an enlarged bowl, the only one application criterion being the need to control a diaphragm of tendrils on injection devices with variable geometry arranged in a crown on the bottom of an annular combustion chamber.

De la même manière des injecteurs de types différents peuvent être combinés avec les dispositifs à bols intermédiaires précédemment mentionnés.In the same way, injectors of different types can be combined with the devices with intermediate bowls previously mentioned.

Claims (9)

1. Chambre de combustion annulaire, notamment pour turbomachines comportant une série d'injecteurs (4) d'air et de carburant d'axes parallèles à l'axe de symétrie longitudinale de la chambre, régulièrement répartis en couronne sur le fond de chambre (3), chaque injecteur possédant une vrille de turbulence externe (11) destinée à l'introduction dans le dispositif d'injection d'une première fraction d'air pour former un mélange combustible air-carburant, lesdites vrilles de turbulence externe (11) étant formées d'ailettes définissant des canaux pouvant être obturés par un diaphragme (13) mobile en rotation autour de l'injecteur, la chambre de combustion comportant sur la partie radialement externe de son fond de chambre une virole circulaire (5), appelée casquette à section en quart de rond orienté vers l'aval, ladiate casquette étant apte à assurer le guidage de la première fraction (F1) de l'air comprimé dans la veine vers le dispositif d'injection (4) et d'une seconde fraction (F2) dudit air comprimé vers la paroi externe (2) de la chambre de combustion pour en assurer le refroidissement par convection externe, caractérisée en ce que la casquette (5) est rendue mobile en rotation autour de l'axe de symétrie longitudinale de la chambre de combustion sous l'action d'un premier moyen de commande (20,22,23) et comporte des seconds moyens (13a,21) pour entrainer en rotation simultanément chaque diaphragme (13) porté par la vrille (11) de turbulence externe de chaque injecteur autour de l'axe de ce dernier.1. Annular combustion chamber, in particular for turbomachines comprising a series of injectors (4) of air and fuel with axes parallel to the longitudinal axis of symmetry of the chamber, regularly distributed in a crown on the chamber bottom ( 3), each injector having an external swirl swirl (11) intended for the introduction into the injection device of a first fraction of air to form a combustible air-fuel mixture, said swirl swirls (11) being formed of fins defining channels which can be closed by a diaphragm (13) movable in rotation around the injector, the combustion chamber comprising on the radially external part of its chamber bottom a circular ferrule (5), called cap with quarter-round section facing downstream, the cap cap being able to guide the first fraction (F1) of the compressed air in the vein towards the injection device (4) and a second fraction (F2) from said compressed air towards the external wall (2) of the combustion chamber to cool it by external convection, characterized in that the cap (5) is made to rotate in rotation around the longitudinal axis of symmetry of the combustion chamber combustion under the action of a first control means (20,22,23) and comprises second means (13a, 21) for simultaneously driving in rotation each diaphragm (13) carried by the spin (11) of external turbulence of each injector around the axis of the latter. 2. Chambre de combustion selon la revendication 1 caractérisée en ce que le premier moyen de commande en rotation de la casquette (5) est constitué par une rotule radiale unique (23) portée par la casquette (5) et coopérant avec une fourchette (22) montée à l'extrémité d'un arbre tournant (20) traversant le carter externe (6) entourant la chambre de combustion, ledit bras étant actionné en rotation par un moyen mécanique.2. Combustion chamber according to claim 1 characterized in that the first means for controlling the rotation of the cap (5) consists of a single radial ball joint (23) carried by the cap (5) and cooperating with a fork (22 ) mounted at the end a rotating shaft (20) passing through the external casing (6) surrounding the combustion chamber, said arm being actuated in rotation by mechanical means. 3. Chambre de combustion selon l'une quelconque des revendications 1 ou 2, caractérisée en ce que les seconds moyens pour entrainer en rotation simultanément tous les diaphragmes (13) sont constitués par des ergots (21) régulièrement répartis sur la partie amont de la casquette (5), le nombre d'ergots étant égal à celui des diaphragmes dont le mouvement en rotation doit être commandé, chaque ergot coopérant avec une fourchette (13a) portée par le diaphragme (13) qu'il commande.3. Combustion chamber according to any one of claims 1 or 2, characterized in that the second means for simultaneously driving in rotation all the diaphragms (13) consist of lugs (21) regularly distributed over the upstream part of the cap (5), the number of pins being equal to that of the diaphragms whose rotational movement must be controlled, each pin cooperating with a fork (13a) carried by the diaphragm (13) which it controls. 4. Chambre de combustion selon la revendication 3 caractérisée en ce que chaque ergot (21) est vissé dans la casquette (5) et comporte une extrémité (21a) coopérant avec la fourchette (13a) du diaphragme, ladite extrémité (21a) étant excentrée par rapport au filetage de l'ergot pour permettre le réglage de simultanéité de mise en rotation de tous les diaphragmes, et en ce que chaque ergot comporte des moyens de blocage (25) sur la casquette dans sa position de règlage optimal.4. Combustion chamber according to claim 3 characterized in that each lug (21) is screwed into the cap (5) and has one end (21a) cooperating with the fork (13a) of the diaphragm, said end (21a) being eccentric relative to the thread of the lug to allow the adjustment of simultaneous rotation of all the diaphragms, and in that each lug has locking means (25) on the cap in its optimal adjustment position. 5. Chambre de combustion selon l'une quelconque des revendications 1 à 4 caractérisée en ce qu'un moyen de palier tournant (14,15 ; 30) est interposé entre la casquette (5) et la paroi externe (2) de la chambre de combustion.5. Combustion chamber according to any one of claims 1 to 4 characterized in that a rotary bearing means (14,15; 30) is interposed between the cap (5) and the external wall (2) of the chamber combustion. 6. Chambre de combustion selon la revendication 5, caractérisée en ce que le moyen de palier tournant est disposé entre une première piste circulaire (17) biconique interne de la casquette (5) et une seconde piste circulaire biconique formée par l'extrémité tronconique (2a) de la paroi externe de la chambre et par une portée tronconique (18a) d'un anneau interne (18) disposé sous la paroi de la chambre sur laquelle il est solidarisé.6. Combustion chamber according to claim 5, characterized in that the rotary bearing means is disposed between a first circular biconic track (17) internal of the cap (5) and a second track biconical circular formed by the frustoconical end (2a) of the external wall of the chamber and by a frustoconical bearing (18a) of an internal ring (18) disposed under the wall of the chamber on which it is secured. 7. Chambre de combustion selon la revendication 6 caractérisée en ce que le moyen de palier tournant est constitué par un anneau (30) réalisé en un matériau antifriction, résistant à chaud.7. Combustion chamber according to claim 6 characterized in that the rotary bearing means is constituted by a ring (30) made of an antifriction material, resistant to heat. 8. Chambre de combustion selon la revendication 6, caractérisée en ce que le moyen de palier tournant est constitué par une couronne à billes (14,15) en contact de roulement avec la première et la seconde pistes circulaires biconiques.8. Combustion chamber according to claim 6, characterized in that the rotary bearing means is constituted by a ball ring (14,15) in rolling contact with the first and second biconical circular tracks. 9. Chambre de combustion selon la revendiation 8, caractérisée en ce que la couronne à billes comporte une cage circulaire (14) de positionnement des billes et en ce que l'anneau interne comporte un orifice (18b) d'introduction des billes dans la cage (14) lors du montage de la couronne à billes, ledit orifice étant effacé sous la paroi de la chambre lorsque l'anneau interne (18) est solidarisé à cette dernière.9. Combustion chamber according to claim 8, characterized in that the ball ring comprises a circular cage (14) for positioning the balls and in that the internal ring comprises an orifice (18b) for introducing the balls into the cage (14) during assembly of the ball ring, said orifice being erased under the wall of the chamber when the internal ring (18) is secured to the latter.
EP87401444A 1986-07-03 1987-06-24 Annular gas turbine combustor having a controlling device for the primary air Expired EP0251895B1 (en)

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FR8609652A FR2601115B1 (en) 1986-07-03 1986-07-03 ANNULAR COMBUSTION CHAMBER COMPRISING A SINGLE CONTROL MEANS FOR INJECTOR DIAPHRAGMS
FR8609652 1986-07-03

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FR2572463A1 (en) * 1984-10-30 1986-05-02 Snecma INJECTION SYSTEM WITH VARIABLE GEOMETRY.

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1992017736A1 (en) * 1991-03-30 1992-10-15 MTU MOTOREN- UND TURBINEN-UNION MüNCHEN GMBH Gas turbine combustor
US5490378A (en) * 1991-03-30 1996-02-13 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Gas turbine combustor
DE4228816A1 (en) * 1992-08-29 1994-03-03 Mtu Muenchen Gmbh Burners for gas turbine engines
US5357743A (en) * 1992-08-29 1994-10-25 Mtu Motoren-Und Turbinen-Union Muenchen Gmbh Burner for gas turbine engines
US5373693A (en) * 1992-08-29 1994-12-20 Mtu Motoren- Und Turbinen-Union Munchen Gmbh Burner for gas turbine engines with axially adjustable swirler
DE4228816C2 (en) * 1992-08-29 1998-08-06 Mtu Muenchen Gmbh Burners for gas turbine engines
FR3141755A1 (en) 2022-11-08 2024-05-10 Safran Aircraft Engines Combustion chamber of a turbomachine

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FR2601115B1 (en) 1988-09-02
EP0251895B1 (en) 1989-10-11
FR2601115A1 (en) 1988-01-08
US4825641A (en) 1989-05-02
DE3760766D1 (en) 1989-11-16

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