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EP2307805B1 - Gas turbine engine combustion chamber comprising cmc deflectors - Google Patents

Gas turbine engine combustion chamber comprising cmc deflectors Download PDF

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Publication number
EP2307805B1
EP2307805B1 EP09772283.9A EP09772283A EP2307805B1 EP 2307805 B1 EP2307805 B1 EP 2307805B1 EP 09772283 A EP09772283 A EP 09772283A EP 2307805 B1 EP2307805 B1 EP 2307805B1
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EP
European Patent Office
Prior art keywords
deflector
combustion chamber
sleeve
chamber
cup
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.)
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Application number
EP09772283.9A
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German (de)
French (fr)
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EP2307805A2 (en
Inventor
Sylvain Duval
Didier Hyppolyte Hernandez
Romain Nicolas Lunel
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
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Safran Aircraft Engines SAS
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Publication of EP2307805A2 publication Critical patent/EP2307805A2/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances

Definitions

  • the present invention relates to the field of gas turbine engines and in particular that of the combustion chambers of such engines.
  • the combustion chamber of a gas turbine engine receives compressed air from the upstream high pressure compressor and provides a combustion-heated gas in a fuel-fired combustion zone.
  • the chamber thus comprises an upstream chamber bottom wall on which the different fuel injection systems are fixed.
  • the figure 1 shows a chamber of the prior art.
  • the annular chamber 1 is housed inside a housing 2 of the engine downstream of the diffuser 3 of compressed air. It comprises an inner wall 4 and an outer wall 5 delimiting between them a combustion zone.
  • the chamber In its upstream part the chamber comprises a transverse wall 6 of bottom chamber on which are provided openings each equipped with a system 7 for supplying carbureted air.
  • Such a system is supplied with fuel from a liquid fuel injector and includes concentric annular grids to create swirling air streams promoting their mixing with the sprayed fuel web.
  • Part of the air from the diffuser is diverted from the fuel intake zone through the shroud 8 and flows along and out of the outer wall as well as along and out of the inner wall.
  • the primary combustion zone is therefore immediately downstream of the wall of the chamber bottom.
  • Deflectors 9 made of metallic material line the inside of the wall of the chamber bottom and serve to protect it from the intense radiation produced in the primary combustion zone.
  • Air is introduced through orifices made in the wall of the chamber bottom behind the baffles to ensure their cooling. This air flows along the rear face of the baffles and is then guided to form a film along the longitudinal outer walls of the chamber.
  • a gas turbine engine combustion chamber according to the preamble of claim 1 is shown in US 6,212,870 B1 .
  • baffle CMC ceramic matrix composite
  • CMCs ceramic matrix components
  • They are formed of a carbon fiber reinforcement or refractory material and a ceramic matrix.
  • the manufacture of a CMC comprises the production of a fiber preform intended to constitute the reinforcement of the structure, and the densification of the preform by the ceramic material of the matrix.
  • CMCs have the advantage of maintaining their mechanical properties up to high temperatures in an oxidizing medium.
  • a CMC has a thermal expansion rate four times lower than the metal used for the chamber.
  • this material can not be welded or soldered.
  • the applicant has set a goal to develop a manner of mounting deflectors of CMC type material on the bottom wall of a combustion chamber.
  • this object is achieved with a combustion chamber having the features reported in the main claim.
  • the sheath is preferably fixed by brazing to the wall and the mechanical attachment means is interconnection.
  • the cup comprises a radial flange through which it is fixed by welding to the metal sleeve.
  • the carbureted air supply system comprises a bowl fixed by a flange to the metal sheath.
  • the mechanical attachment means of the baffle cooperates with a deflector support attached to the sleeve.
  • This support forms an intermediate piece which makes it possible to move the brazing zones away from the metal parts without damaging the CMC material constituting the deflector.
  • the cylindrical portion of the deflector is integral with a cylindrical element forming a cup, housed, with cold play, inside the annular flange of the deflector, said cup member ensuring the guiding of the deflector when the temperature has increased.
  • a chamber bottom according to one embodiment of the invention is shown.
  • the bottom wall 11 of the chamber 10 is protected from the radiation of the combustion zone by a deflector 12 made of CMC material.
  • the shape of the deflector is substantially the same as that of the deflector 9 of the prior art with a generally flat portion 12A which is placed parallel to the wall 11 and two portions 12b curved towards the outer and inner walls.
  • the deflector 12 is open in its central part with a cylindrical portion 12c having the same axis as the fuel air supply system 13.
  • a metal sleeve 14 In the opening of the wall 11 of the chamber bottom, is fixed a metal sleeve 14.
  • a solder 14a holds the sleeve 14 against the inner edge of the opening of the wall 11.
  • the sleeve comprises a cylindrical portion 14b and a portion radial 14c, the latter providing a space with a stopper 15 which is welded to its periphery.
  • 14d transverse teeth facing the axis of the opening of the wall 11 are formed inside the cylindrical portion 14b of the sleeve 14.
  • a centering cup 16 comprises a cylindrical portion 16a and a flange 16b radial and transverse. The cup 16 is disposed inside the cylindrical portion 14b of the sleeve and fixed by a weld bead 16c peripheral to the sleeve 14.
  • the cylindrical portion 16a of the cup is inside the cylindrical portion 12c.
  • the deflector 12 comprises a transverse groove 12c1 on the outer face of the cylindrical portion 12c, forming housing teeth 14d of the sleeve.
  • the groove is perforated to allow the axial passage of the teeth 14d to the assembly and the locking by rotation of the sleeve relative to the cylindrical portion 12c of the baffle 12.
  • This mechanical fastening mode from the baffle to the sheath is of the type interconnection. Other modes of mechanical fixing are possible.
  • the cylindrical portion 16a of the cup is inside the cylindrical portion 12c, with mounting a radial clearance.
  • the device for injecting and carburizing air is represented generally by the reference 13. It is not detailed to the extent that the subject of the invention does not concern it.
  • the diverging bowl 13a of the device comprises externally a transverse flange 13b housed in the space formed between the radial face 14c of the sleeve 14 and the stopper 15.
  • the sheath 14 is fixed, figure 5 , brazing it on the chamber bottom with the solder bead 14a, figure 2 and an anti-rotation pin 18 is placed between the diameter of the sleeve and that of the deflector.
  • the centering cup 16 is slid into the cylindrical portion 12c of the deflector. And the cup is fixed by a point or a weld bead 16c between the latter and the sleeve 14.
  • the fuel injection device 13 is mounted that is immobilized by the stop plate 15. It is welded to the sheath.
  • This mounting mode of the deflector makes it possible to immobilize it in the wall of the chamber bottom by a mechanical means of attachment.
  • the welds are made only between the metal parts. Differential expansion of the deflectors with respect to the metallic environment is taken into account by means of the centering cup which, by expanding radially, immobilizes the deflector in position.
  • the clearance between the sleeve and the baffle on the one hand and the baffle and the centering cup on the other hand are to be optimized according to the operating temperatures and the diameter of the parts.
  • the assembly principle is generally the same as before; we simply modified the sheath and the cup.
  • a baffle support sleeve 26, annular, comprises transverse teeth 26d cooperating with the outer groove 12c1 of the annular flange of the deflector.
  • the support sleeve 26 is slid axially from the outside of the chamber with introduction of the teeth 26d into the groove 12c1 by the openings (not visible) of the groove.
  • a rotation around the axis of the opening allows the interconnection of the support sleeve 26 with the deflector.
  • the support sleeve 26 has a cylindrical portion 26a, forming a cylindrical centering cup radially inner which fits inside the flange 12c. In cold mounting, a clearance is provided between the cylindrical portion 26a of the support sleeve and the flange 12c of the deflector. The centering is ensured by the mechanical attachment to clutch.
  • the deflector support sleeve expands more than the deflector CMC material.
  • the cylindrical portion bears against the inner face of the clamp 12c with clamping and ensures the centering of the deflector.
  • the fuel injection device 13 is mounted as before by the outside of the chamber, a transverse flange 13b being immobilized between the rear face of the deflector support 26 and a stop cup 15 brazed to the support.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Cylinder Crankcases Of Internal Combustion Engines (AREA)

Description

La présente invention concerne le domaine des moteurs à turbine à gaz et en particulier celui des chambres de combustion de tels moteurs.The present invention relates to the field of gas turbine engines and in particular that of the combustion chambers of such engines.

La chambre de combustion d'un moteur à turbine à gaz reçoit l'air comprimé issu du compresseur à haute pression amont et fournit un gaz réchauffé par combustion dans une zone de combustion alimentée en carburant. La chambre comprend ainsi une paroi de fond de chambre située en amont sur laquelle sont fixés les différents systèmes d'injection de carburant. La figure 1 montre une chambre de l'art antérieur. La chambre 1 annulaire est logée à l'intérieur d'un carter 2 du moteur en aval du diffuseur 3 d'air comprimé. Elle comprend une paroi intérieure 4 et une paroi extérieure 5 délimitant entre elles une zone de combustion. Dans sa partie amont la chambre comprend une paroi 6 transversale de fond de chambre sur laquelle sont ménagées des ouvertures équipées chacune d'un système 7 d'alimentation en air carburé. Un tel système est alimenté en carburant depuis un injecteur de carburant liquide et comprend des grilles annulaires concentriques pour créer des flux d'air tourbillonnant favorisant leur mélange avec la nappe de carburant pulvérisé.The combustion chamber of a gas turbine engine receives compressed air from the upstream high pressure compressor and provides a combustion-heated gas in a fuel-fired combustion zone. The chamber thus comprises an upstream chamber bottom wall on which the different fuel injection systems are fixed. The figure 1 shows a chamber of the prior art. The annular chamber 1 is housed inside a housing 2 of the engine downstream of the diffuser 3 of compressed air. It comprises an inner wall 4 and an outer wall 5 delimiting between them a combustion zone. In its upstream part the chamber comprises a transverse wall 6 of bottom chamber on which are provided openings each equipped with a system 7 for supplying carbureted air. Such a system is supplied with fuel from a liquid fuel injector and includes concentric annular grids to create swirling air streams promoting their mixing with the sprayed fuel web.

Une partie de l'air issu du diffuseur est déviée de la zone d'admission du carburant par le carénage 8 et s'écoule le long et à l'extérieur de la paroi extérieure aussi bien que le long et à l'extérieur de la paroi intérieure.Part of the air from the diffuser is diverted from the fuel intake zone through the shroud 8 and flows along and out of the outer wall as well as along and out of the inner wall.

La partie qui passe à l'intérieur de la zone de carburation, franchit la paroi 6 de fond de chambre, et le mélange est allumé par des bougies disposées sur la paroi annulaire extérieure. La zone de combustion primaire se situe donc immédiatement en aval de la paroi du fond de chambre. Des déflecteurs 9 en matériau métallique tapissent l'intérieur de la paroi du fond de chambre et ont pour fonction de la protéger du rayonnement intense produit dans la zone de combustion primaire. De l'air est introduit par des orifices pratiqués dans la paroi du fond de chambre en arrière des déflecteurs pour assurer leur refroidissement. Cet air s'écoule le long de la face arrière des déflecteurs et est ensuite guidé pour former un film le long des parois extérieures longitudinales de la chambre.The part which passes inside the carburizing zone, crosses the wall 6 of chamber bottom, and the mixture is ignited by candles arranged on the outer annular wall. The primary combustion zone is therefore immediately downstream of the wall of the chamber bottom. Deflectors 9 made of metallic material line the inside of the wall of the chamber bottom and serve to protect it from the intense radiation produced in the primary combustion zone. Air is introduced through orifices made in the wall of the chamber bottom behind the baffles to ensure their cooling. This air flows along the rear face of the baffles and is then guided to form a film along the longitudinal outer walls of the chamber.

Une chambre de combustion de moteur de turbine à gaz selon le préambule de la revendication 1 est montrée dans US 6 212 870 B1 .A gas turbine engine combustion chamber according to the preamble of claim 1 is shown in US 6,212,870 B1 .

Dans la mesure où les déflecteurs de fond de chambre ne sont pas sollicités mécaniquement, n'ont pas de rôle structural et ont une seule fonction de protection thermique, et dans la recherche d'une optimisation des flux d'air, on souhaiterait pouvoir réduire le flux le long de la paroi du fond de chambre et en affecter une fraction à une autre fonction, notamment de refroidissement des parois intérieures ou extérieures.Insofar as the chamber bottom deflectors are not mechanically stressed, have no structural role and have a single function of thermal protection, and in the search for an optimization of the air flows, it would be desirable to be able to reduce the flow along the wall of the chamber bottom and to affect a fraction of it to another function, in particular of cooling the internal or external walls. .

Par ailleurs, les performances des moteurs en constante amélioration conduisent à entretenir des températures de chambre de plus en plus élevées. Afin de respecter les spécifications de durée de vie de la chambre, il serait nécessaire d'intensifier le refroidissement des parois et du déflecteur de fond de chambre. La solution d'augmenter le débit de refroidissement serait pénalisante pour le rendement de la chambre.In addition, engine performance is constantly improving and leads to higher and higher chamber temperatures. In order to comply with the specifications of the service life of the chamber, it would be necessary to intensify the cooling of the walls and the bottom chamber deflector. The solution of increasing the cooling rate would be detrimental to the efficiency of the chamber.

Pour résoudre ce problème il est proposé de remplacer le déflecteur métallique connu par un déflecteur en CMC (Composite à matrice Céramique). La tenue à haute température de ce matériau est bien meilleure que celle du métal. Cette solution permettrait de maîtriser le débit d'air de refroidissement des déflecteurs et, à même température de fonctionnement de la chambre, de le diminuer pour en affecter une partie à une autre fonction ou bien d'accepter des températures de fonctionnement plus élevées pour un même débit d'air de refroidissement.To solve this problem it is proposed to replace the known metal baffle with a baffle CMC (ceramic matrix composite). The high temperature behavior of this material is much better than that of the metal. This solution would make it possible to control the cooling air flow of the baffles and, at the same operating temperature of the chamber, to reduce it in order to affect part of it to another function or to accept higher operating temperatures for same cooling air flow.

Les CMC, composants à matrice céramique, sont en soi connus. Ils sont formés d'un renfort en fibres de carbone ou bien en matière réfractaire et d'une matrice céramique. La fabrication d'un CMC comprend la réalisation d'une préforme fibreuse destinée à constituer le renfort de la structure, et la densification de la préforme par le matériau céramique de la matrice. Les CMC présentent l'avantage de conserver leurs propriétés mécaniques jusqu'à des températures élevées en milieu oxydant.CMCs, ceramic matrix components, are known per se. They are formed of a carbon fiber reinforcement or refractory material and a ceramic matrix. The manufacture of a CMC comprises the production of a fiber preform intended to constitute the reinforcement of the structure, and the densification of the preform by the ceramic material of the matrix. CMCs have the advantage of maintaining their mechanical properties up to high temperatures in an oxidizing medium.

Le montage d'une pièce de ce type dans une structure métallique présente toutefois des difficultés en raison notamment de la différence importante de leur coefficient de dilatation. Un CMC a un taux de dilatation thermique quatre fois plus faible que celui du métal utilisé pour la chambre. Par ailleurs ce matériau ne peut pas être soudé ou brasé.The mounting of a piece of this type in a metal structure, however, presents difficulties because of the large difference in their coefficient of expansion. A CMC has a thermal expansion rate four times lower than the metal used for the chamber. In addition, this material can not be welded or soldered.

La demanderesse s'est fixé comme objectif de mettre au point un mode de montage de déflecteurs en matériau de type CMC sur la paroi de fond d'une chambre de combustion.The applicant has set a goal to develop a manner of mounting deflectors of CMC type material on the bottom wall of a combustion chamber.

Conformément à l'invention, on parvient à cet objectif avec une chambre de combustion présentant les caractéristiques rapportées dans la revendication principale.According to the invention, this object is achieved with a combustion chamber having the features reported in the main claim.

Le fourreau est de préférence fixé par brasage à la paroi et le moyen d'accrochage mécanique est à crabotage. Des dents radiales sur l'une des deux pièces, partie cylindrique du déflecteur ou fourreau métallique, coopèrent avec une rainure sur l'autre pièce.The sheath is preferably fixed by brazing to the wall and the mechanical attachment means is interconnection. Radial teeth on one of the two parts, cylindrical part of the deflector or metal sleeve, cooperate with a groove on the other part.

On assure ainsi le maintien du déflecteur sans brasage.This ensures the maintenance of the deflector without soldering.

Cette solution permet, aux températures élevées, de maintenir en position le déflecteur contre le fourreau. En effet en se dilatant la coupelle vient en prise avec la partie cylindrique du déflecteur.This solution makes it possible, at high temperatures, to keep the deflector in position against the sheath. Indeed by expanding the cup engages with the cylindrical portion of the deflector.

Plus particulièrement, la coupelle comprend une bride radiale par laquelle elle est fixée par soudage au fourreau métallique.More particularly, the cup comprises a radial flange through which it is fixed by welding to the metal sleeve.

Le système d'alimentation en air carburé comprend un bol fixé par une bride au fourreau métallique.The carbureted air supply system comprises a bowl fixed by a flange to the metal sheath.

Conformément à une variante de réalisation, le moyen de fixation mécanique du déflecteur coopère avec un support de déflecteur rapporté sur le fourreau. Ce support forme une pièce intermédiaire qui permet d'éloigner les zones de brasage des pièces métalliques entre elles sans risquer d'endommager le matériau CMC constituant le déflecteur.According to an alternative embodiment, the mechanical attachment means of the baffle cooperates with a deflector support attached to the sleeve. This support forms an intermediate piece which makes it possible to move the brazing zones away from the metal parts without damaging the CMC material constituting the deflector.

Comme dans la réalisation précédente, la partie cylindrique du déflecteur est solidaire d'un élément cylindrique, formant coupelle, logé, avec jeu à froid, à l'intérieur de la bride annulaire du déflecteur, ledit élément formant coupelle assurant le guidage du déflecteur quand la température a augmenté.As in the previous embodiment, the cylindrical portion of the deflector is integral with a cylindrical element forming a cup, housed, with cold play, inside the annular flange of the deflector, said cup member ensuring the guiding of the deflector when the temperature has increased.

On décrit maintenant plus en détail deux formes, non limitatives, de réalisation de l'invention en référence aux dessins annexés sur lesquels :

  • la figure 1 représente en demi-coupe axiale une chambre de combustion d'un moteur à turbine à gaz de l'art antérieur,
  • la figure 2 représente partiellement le fond de chambre selon l'invention en coupe axiale, avec une loupe qui montre plus en détail la zone de montage du déflecteur dans le fond de chambre,
  • les figures 3 à 6 montrent la succession des étapes de montage du déflecteur dans le fond de chambre,
  • la figure 7 montre en coupe axiale une variante de réalisation de l'invention.
Two non-limiting embodiments of the invention will now be described in greater detail with reference to the accompanying drawings in which:
  • the figure 1 represents in axial half-section a combustion chamber of a gas turbine engine of the prior art,
  • the figure 2 partially shows the chamber bottom according to the invention in axial section, with a magnifying glass which shows in more detail the mounting area of the deflector in the chamber bottom,
  • the Figures 3 to 6 show the succession of steps of mounting the deflector in the chamber bottom,
  • the figure 7 shows in axial section an alternative embodiment of the invention.

En se reportant à la figure 2, on voit un fond de chambre conforme à un mode de réalisation de l'invention. La paroi 11 de fond de la chambre 10 est protégée du rayonnement de la zone de combustion par un déflecteur 12 en matériau CMC. La forme du déflecteur est sensiblement la même que celle du déflecteur 9 de l'art antérieur avec une partie généralement plane 12A qui vient se placer parallèlement à la paroi 11 et deux parties 12b incurvées vers les parois extérieure et intérieure. Le déflecteur 12 est ouvert dans sa partie centrale avec une partie cylindrique 12c de même axe que le système d'alimentation en air carburé 13.Referring to the figure 2 a chamber bottom according to one embodiment of the invention is shown. The bottom wall 11 of the chamber 10 is protected from the radiation of the combustion zone by a deflector 12 made of CMC material. The shape of the deflector is substantially the same as that of the deflector 9 of the prior art with a generally flat portion 12A which is placed parallel to the wall 11 and two portions 12b curved towards the outer and inner walls. The deflector 12 is open in its central part with a cylindrical portion 12c having the same axis as the fuel air supply system 13.

Dans l'ouverture de la paroi 11 de fond de chambre, est fixé un fourreau métallique 14. Une brasure 14a maintient le fourreau 14 contre le bord intérieur de l'ouverture de la paroi 11. Le fourreau comprend une partie cylindrique 14b et une partie radiale 14c, cette dernière ménageant un espace avec une coupelle d'arrêt 15 qui est soudée à sa périphérie. Des dents 14d transversales tournées vers l'axe de l'ouverture de la paroi 11 sont ménagées à l'intérieur de la partie cylindrique 14b du fourreau 14. Une coupelle de centrage 16 comprend une partie cylindrique 16a et une bride 16b radiale et transversale. La coupelle 16 est disposée à l'intérieur de la partie cylindrique 14b du fourreau et fixée par un cordon de soudure 16c périphérique au fourreau 14. La partie cylindrique 16a de la coupelle est à l'intérieur de la partie cylindrique 12c.In the opening of the wall 11 of the chamber bottom, is fixed a metal sleeve 14. A solder 14a holds the sleeve 14 against the inner edge of the opening of the wall 11. The sleeve comprises a cylindrical portion 14b and a portion radial 14c, the latter providing a space with a stopper 15 which is welded to its periphery. 14d transverse teeth facing the axis of the opening of the wall 11 are formed inside the cylindrical portion 14b of the sleeve 14. A centering cup 16 comprises a cylindrical portion 16a and a flange 16b radial and transverse. The cup 16 is disposed inside the cylindrical portion 14b of the sleeve and fixed by a weld bead 16c peripheral to the sleeve 14. The cylindrical portion 16a of the cup is inside the cylindrical portion 12c.

Le déflecteur 12 comprend une rainure transversale 12c1 sur la face extérieure de la partie cylindrique 12c, formant logement des dents 14d du fourreau. La rainure est ajourée pour permettre le passage axial des dents 14d au montage puis le verrouillage par rotation du fourreau par rapport à la partie cylindrique 12c du déflecteur 12. Ce mode de fixation mécanique du déflecteur au fourreau est du type à crabotage. D'autres modes de fixation mécanique sont envisageables. Comme on le voit sur la figure 2a la partie cylindrique 16a de la coupelle est à l'intérieur de la partie cylindrique 12c, avec au montage un jeu radial.The deflector 12 comprises a transverse groove 12c1 on the outer face of the cylindrical portion 12c, forming housing teeth 14d of the sleeve. The groove is perforated to allow the axial passage of the teeth 14d to the assembly and the locking by rotation of the sleeve relative to the cylindrical portion 12c of the baffle 12. This mechanical fastening mode from the baffle to the sheath is of the type interconnection. Other modes of mechanical fixing are possible. As we see on the figure 2a the cylindrical portion 16a of the cup is inside the cylindrical portion 12c, with mounting a radial clearance.

Le dispositif d'injection et de carburation de l'air est représenté globalement par la référence 13. Il n'est pas détaillé dans la mesure où l'objet de l'invention ne le concerne pas. Le bol divergent 13a du dispositif comprend extérieurement une bride transversale 13b logée dans l'espace formé entre la face radiale 14c du fourreau 14 et la coupelle d'arrêt 15.The device for injecting and carburizing air is represented generally by the reference 13. It is not detailed to the extent that the subject of the invention does not concern it. The diverging bowl 13a of the device comprises externally a transverse flange 13b housed in the space formed between the radial face 14c of the sleeve 14 and the stopper 15.

On décrit le montage de l'ensemble.The assembly of the assembly is described.

On dispose, figure 3, le fourreau 14 contre la paroi 11 du fond de chambre extérieurement à la chambre. Il est centré sur le bord intérieur de l'ouverture correspondante de la paroi 11.We dispose, figure 3 , the sleeve 14 against the wall 11 of the chamber bottom externally to the chamber. It is centered on the inner edge of the corresponding opening of the wall 11.

On met en place, figure 4, le déflecteur 12 dans le fourreau 14 par l'intérieur de la chambre. On introduit axialement les dents 14d par les ajours dans la rainure 12c1. On fait tourner le fourreau 14 de manière à verrouiller les dents axialement par rapport à la bride annulaire 12c. Le fourreau 14 est alors craboté dans le déflecteur 12 par la coopération des dents 14d et de la rainure 12c1.We put in place, figure 4 , the deflector 12 in the sleeve 14 from the inside of the chamber. The teeth 14d are inserted axially through the openings in the groove 12c1. The sleeve 14 is rotated so as to lock the teeth axially relative to the annular flange 12c. The sleeve 14 is then engaged in the deflector 12 by the cooperation of the teeth 14d and the groove 12c1.

On fixe le fourreau 14, figure 5, en le brasant sur le fond de chambre avec le cordon de brasure 14a, figure 2 et un pion 18 anti-rotation est placé entre le diamètre du fourreau et celui du déflecteur. On glisse la coupelle de centrage 16 dans la partie cylindrique 12c du déflecteur. Et on fixe la coupelle par un point ou un cordon de soudure 16c entre celle-ci et le fourreau 14.The sheath 14 is fixed, figure 5 , brazing it on the chamber bottom with the solder bead 14a, figure 2 and an anti-rotation pin 18 is placed between the diameter of the sleeve and that of the deflector. The centering cup 16 is slid into the cylindrical portion 12c of the deflector. And the cup is fixed by a point or a weld bead 16c between the latter and the sleeve 14.

On monte alors le dispositif d'injection de carburant 13 que l'on immobilise par la coupelle d'arrêt 15. Celle-ci est soudée au fourreau.Then the fuel injection device 13 is mounted that is immobilized by the stop plate 15. It is welded to the sheath.

Ce mode de montage du déflecteur permet d'immobiliser celui-ci dans la paroi du fond de chambre par un moyen mécanique d'accrochage. Les soudures sont effectuées uniquement entre les parties métalliques. On tient compte de la dilation différentielle des déflecteurs par rapport à l'environnement métallique grâce à la coupelle de centrage qui en se dilatant radialement vient immobiliser le déflecteur en position.This mounting mode of the deflector makes it possible to immobilize it in the wall of the chamber bottom by a mechanical means of attachment. The welds are made only between the metal parts. Differential expansion of the deflectors with respect to the metallic environment is taken into account by means of the centering cup which, by expanding radially, immobilizes the deflector in position.

Les jeux entre le fourreau et le déflecteur d'une part et le déflecteur et la coupelle de centrage d'autre part sont à optimiser en fonction des températures de fonctionnement et du diamètre des pièces.The clearance between the sleeve and the baffle on the one hand and the baffle and the centering cup on the other hand are to be optimized according to the operating temperatures and the diameter of the parts.

On décrit maintenant une variante de réalisation en référence avec la figure 7.An embodiment variant is now described with reference to the figure 7 .

Le principe de montage est globalement le même que précédemment ; on a simplement modifié le fourreau et la coupelle.The assembly principle is generally the same as before; we simply modified the sheath and the cup.

Le déflecteur 12 et la paroi 11 de fond de chambre sont inchangés. Un fourreau intermédiaire 24 est mis en place dans l'ouverture de la paroi 11 par l'extérieur de la chambre ; il est brasé en 24a le long du bord de l'ouverture. Le déflecteur est introduit dans le fourreau intermédiaire (24) par l'intérieur de la chambre. Un fourreau support de déflecteur 26, annulaire, comprend des dents transversales 26d coopérant avec la rainure extérieure 12c1 de la bride annulaire du déflecteur. Le fourreau support 26 est glissé axialement par l'extérieur de la chambre avec introduction des dents 26d dans la rainure 12c1 par les ajours (non visibles) de la rainure. Une rotation atour de l'axe de l'ouverture permet le crabotage du fourreau support 26 avec le déflecteur. Pour maintenir la liaison mécanique entre le fourreau support et le déflecteur, il suffit de souder en 26b le fourreau support 26 au fourreau intermédiaire 24 à la périphérie qui est éloignée du déflecteur en CMC.The deflector 12 and the wall 11 of the chamber bottom are unchanged. An intermediate sheath 24 is placed in the opening of the wall 11 by the outside of the chamber; it is brazed at 24a along the edge of the opening. The deflector is introduced into the intermediate sheath (24) from the inside of the chamber. A baffle support sleeve 26, annular, comprises transverse teeth 26d cooperating with the outer groove 12c1 of the annular flange of the deflector. The support sleeve 26 is slid axially from the outside of the chamber with introduction of the teeth 26d into the groove 12c1 by the openings (not visible) of the groove. A rotation around the axis of the opening allows the interconnection of the support sleeve 26 with the deflector. To maintain the mechanical connection between the support sleeve and the deflector, it is sufficient to weld at 26b the support sleeve 26 to the intermediate sheath 24 at the periphery which is remote from the deflector CMC.

Le fourreau support 26 comporte une partie cylindrique 26a, formant coupelle cylindrique de centrage, radialement intérieure qui s'adapte à l'intérieur de la bride 12c. Au montage à froid, un jeu est ménagé entre la partie cylindrique 26a du fourreau support et la bride 12c du déflecteur. Le centrage est assuré par la fixation mécanique à crabot.The support sleeve 26 has a cylindrical portion 26a, forming a cylindrical centering cup radially inner which fits inside the flange 12c. In cold mounting, a clearance is provided between the cylindrical portion 26a of the support sleeve and the flange 12c of the deflector. The centering is ensured by the mechanical attachment to clutch.

A la température de fonctionnement de la chambre de combustion, le fourreau support de déflecteur, notamment, se dilate plus que le déflecteur en matériau CMC. La partie cylindrique vient s'appuyer contre la face interne de la bride 12c avec serrage et assure le centrage du déflecteur.At the operating temperature of the combustion chamber, the deflector support sleeve, in particular, expands more than the deflector CMC material. The cylindrical portion bears against the inner face of the clamp 12c with clamping and ensures the centering of the deflector.

Le dispositif d'injection de carburant 13 est monté comme précédemment par l'extérieur de la chambre, une bride transversale 13b étant immobilisée entre la face arrière du support de déflecteur 26 et une coupelle d'arrêt 15 brasée sur le support.The fuel injection device 13 is mounted as before by the outside of the chamber, a transverse flange 13b being immobilized between the rear face of the deflector support 26 and a stop cup 15 brazed to the support.

Claims (7)

  1. A combustion chamber for a gas turbine engine comprising at least one deflector (12) mounted on the chamber end wall (11) provided with an opening for a carbureted air supply device (13), characterized in that the deflector (12) comprises an opening, corresponding to the chamber end wall opening, with an annular cylindrical part (12c) for attachment to said wall, said cylindrical part (12c) comprising a mechanical fastening means (12cl) collaborating with a complementary fastening means (14d, 26d) on a metal sleeve (14, 26) secured to said wall (11) and a cylindrical centering cup (16a, 26a) fixed by one end to said sleeve (14, 26), characterized in that the cylindrical cup (16a, 26a) is housed with clearance inside the cylindrical part (12c) when the combustion chamber is cold, the clearance becoming smaller if not being eliminated at the combustion chamber operating temperatures.
  2. The combustion chamber as claimed in claim 1, in which the fastening means is of the jaw coupling type.
  3. The combustion chamber as claimed in claim 1 , in which the cup (16a) comprises a radial flange (16b) by which it is fixed by brazing to the metal sleeve (14).
  4. The combustion chamber as claimed in claim 1, in which the carbureted air supply device (13) comprises a bowl (13a) fixed by a flange (13b) to said metal sleeve.
  5. The combustion chamber as claimed in claim 2, in which the jaw coupling means (12cl) of attachment of the deflector (12) collaborates with a deflector support sleeve (26) attached to an intermediate sleeve (24).
  6. The combustion chamber as claimed in the preceding claim, in which the deflector support sleeve (26) is secured to a cup-forming cylindrical element (26a) housed with clearance, when cold, inside the annular cylindrical part (12c) of the deflector, said cup-forming cylindrical element (26a) centering the deflector when the temperature has increased.
  7. The combustion chamber as claimed in claim 5 in which the deflector support sleeve (26) is fixed by brazing some distance away from the deflector.
EP09772283.9A 2008-06-10 2009-06-10 Gas turbine engine combustion chamber comprising cmc deflectors Active EP2307805B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0803226A FR2932251B1 (en) 2008-06-10 2008-06-10 COMBUSTION CHAMBER FOR A GAS TURBINE ENGINE COMPRISING CMC DEFLECTORS
PCT/EP2009/057147 WO2010000583A2 (en) 2008-06-10 2009-06-10 Gas turbine engine combustion chamber comprising cmc deflectors

Publications (2)

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EP2307805A2 EP2307805A2 (en) 2011-04-13
EP2307805B1 true EP2307805B1 (en) 2017-03-15

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EP (1) EP2307805B1 (en)
JP (1) JP5475757B2 (en)
CN (1) CN102057224B (en)
BR (1) BRPI0914905B1 (en)
CA (1) CA2727254C (en)
FR (1) FR2932251B1 (en)
RU (1) RU2507452C2 (en)
WO (1) WO2010000583A2 (en)

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Also Published As

Publication number Publication date
BRPI0914905B1 (en) 2020-05-05
RU2507452C2 (en) 2014-02-20
BRPI0914905A2 (en) 2015-10-20
JP2011523020A (en) 2011-08-04
FR2932251B1 (en) 2011-09-16
WO2010000583A2 (en) 2010-01-07
JP5475757B2 (en) 2014-04-16
EP2307805A2 (en) 2011-04-13
CA2727254C (en) 2016-08-23
CN102057224A (en) 2011-05-11
FR2932251A1 (en) 2009-12-11
WO2010000583A3 (en) 2010-07-29
CN102057224B (en) 2013-04-24
RU2010154030A (en) 2012-07-20
US20110113789A1 (en) 2011-05-19
CA2727254A1 (en) 2010-01-07
US8756935B2 (en) 2014-06-24

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