[go: up one dir, main page]

EP1734305A2 - Assembly of an annular combustion chamber for a turbine - Google Patents

Assembly of an annular combustion chamber for a turbine Download PDF

Info

Publication number
EP1734305A2
EP1734305A2 EP06114424A EP06114424A EP1734305A2 EP 1734305 A2 EP1734305 A2 EP 1734305A2 EP 06114424 A EP06114424 A EP 06114424A EP 06114424 A EP06114424 A EP 06114424A EP 1734305 A2 EP1734305 A2 EP 1734305A2
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
axial
walls
fastening
washer
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
EP06114424A
Other languages
German (de)
French (fr)
Other versions
EP1734305A3 (en
EP1734305B1 (en
Inventor
Mario De Sousa
Didier Hernandez
Laurent Marnas
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1734305A2 publication Critical patent/EP1734305A2/en
Publication of EP1734305A3 publication Critical patent/EP1734305A3/en
Application granted granted Critical
Publication of EP1734305B1 publication Critical patent/EP1734305B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components

Definitions

  • the present invention relates to the general field of turbomachine combustion chambers. It relates more particularly to the problem of assembling an annular combustion chamber whose axial walls and the chamber bottom are made of materials having different coefficients of thermal expansion.
  • composite materials are very expensive and have a fairly low resistance to high mechanical stresses. Also, their use is usually limited only to the axial walls of the combustion chamber, the radial wall (or chamber bottom) bringing upstream these axial walls remaining then more typically made of metallic material.
  • metal materials and composite materials have very different coefficients of thermal expansion. This results in problems in the assembly systems of the combustion chamber between its axial walls of composite material and the metal chamber bottom. In particular, the use of conventional bolting systems is no longer possible from the point of view of the mechanical strength of the walls.
  • the main object of the present invention is therefore to overcome such drawbacks by proposing an assembly system making it possible, in operation, to obtain free expansion of the chamber bottom with respect to the axial walls while ensuring effective damping of the vibrations undergone by the bottom. of room.
  • annular combustion chamber having external and internal axial walls connected upstream by a chamber bottom having a coefficient of thermal expansion different from that of the axial walls, said chamber bottom being provided with a plurality internal and external fastening flanges secured by fastening systems respectively to upstream end portions of the inner and outer walls, each fastening system consisting of a screw passing through one of the fastening flanges and the part upstream end of the corresponding axial wall, and a nut tightened at one end of the fixing screw, characterized in that each fastening system further comprises a sliding sleeve disposed around the fixing screw between the nut and the end portion of the corresponding axial wall, a predetermined radial clearance being provided between the nut and the end portion of the axial wall so as to allow in operation free radial expansion of the chamber bottom relative to the axial walls.
  • each attachment flange comprises a washer made of metallic material which is traversed by the fixing screw and the corresponding sliding bushing, the bushing being made of metallic material.
  • the contact between the bushing and the fastening flange is of metal / metal type. Such contact has the advantage of causing much less wear and repairs of a limited cost compared to a contact of the ceramic / metal type.
  • the contact between the washer of the attachment flanges and the corresponding sliding sleeve is substantially toroidal.
  • This type of contact has the advantage, by avoiding the jamming phenomenon, to facilitate sliding between the bushing and the attachment flange.
  • the washer of the attachment flanges has an extra thickness intended to increase the height of contact between the washer and the corresponding sliding sleeve. The distribution of the contact forces is thus increased, which reduces the wear of the contact between the bushing and the fastening flange.
  • each attachment flange comprises the same preload assembly to provide the chamber bottom stiffness for dynamic stability in the initial operating phase.
  • the fastening systems may comprise means for damping the vibrations in the radial expansion phase of the chamber bottom with respect to the axial walls.
  • Such means may consist of a spiral type spring or blade disposed around the slide sleeve and between the nut and the corresponding fastening flange.
  • Means for sealing between the chamber bottom and the axial walls may also be provided. These means may consist of a lamella-type circular seal mounted in an annular groove formed between the attachment flanges and the end portion of the corresponding axial wall and having a spoiler designed to provide a toric support on the part. end of the axial wall.
  • an inner cap and an outer cap made of composite material extend upstream of the end portion of the respective axial walls, each fastening screw also passing through an orifice formed in the corresponding cap.
  • the present invention also relates to a system for fixing the chamber bottom to the inner and outer axial walls of an annular combustion chamber as defined above.
  • FIG. 1 partially shows in axial section a combustion chamber 10 of a turbomachine in its environment.
  • An outer annular envelope (or outer casing) 12 and an inner annular envelope (or inner casing) 14 coaxial with the latter are centered on the X-X axis of the turbomachine.
  • An annular space 16 formed between these two envelopes receives compressed air according to a general flow F from a compressor (not shown) of the turbomachine through an annular diffusion duct 18. This air is intended for combustion fuel in the chamber 10.
  • a plurality of injection systems 20 regularly distributed around the diffusion duct 18 open into the annular space 16. These injection systems are each provided with a fuel injection nozzle 22 fixed to the outer casing 12. In order to simplification of the drawings, the mixer and the baffle associated with each injection nozzle have not been represented.
  • the combustion chamber 10 of the turbomachine is mounted within this annular space 16 by providing with the outer casings 12 and inner 14 an annular channel 24 for receiving a flow of dilution and cooling air.
  • This chamber is of annular type; it is formed of an outer axial wall 26 and an inner axial wall 28 coaxial with the latter. These axial walls 26, 28 are centered on the X-X axis of the turbomachine.
  • a transverse wall 30 forming a chamber bottom connects upstream the axial walls 26, 28 of the combustion chamber.
  • This chamber bottom 30 is provided with a plurality of openings 32 for the passage of the fuel injection nozzles 22.
  • the chamber bottom 30 and the axial walls 26, 28 are made of materials having very different thermal expansion coefficients.
  • the axial walls may be made of high temperature ceramic material CMC type or other, while the chamber bottom may be made of metal material.
  • the chamber bottom 30 is provided at its ends with a plurality of internal and external flexible hooking flanges 34 which are each attached to the upstream end portions of the axial walls 26, 28. by means of a fixing system 36 of the bolting type.
  • the attachment flanges 34 are in the form of flexible tongues which are integrated in respective rings 38 secured to the chamber bottom 30, for example by welding. They extend upstream beyond the fastening systems 36 and are regularly distributed over the entire circumference of the combustion chamber.
  • the fixing systems 36 each consist of a fastening screw 40 passing through orifices 42, 44 respectively formed in the corresponding fastening flange 34 and in the upstream end portion of the corresponding axial wall 26, 28.
  • a nut 46 is tightened at one end of the fixing screw 40.
  • each fastening system 36 further comprises a sliding sleeve 48 disposed around the fastening screw 40 between the clamping nut 46 and the upstream end portion of the corresponding axial wall 26, 28 of the combustion chamber. Furthermore, a determined radial clearance J is provided between the nut 46 and the upstream end portion of the axial wall 26, 28. Thus, the sliding sleeve 48 has a radial height sufficient to provide such clearance J.
  • the clearance J provided at each attachment system 36 of the combustion chamber in operation makes it possible to obtain radial free expansion of the chamber bottom 30 with respect to the axial walls 26, 28. Such an expansion is made necessary by the fact that that the chamber bottom 30 has a coefficient of thermal expansion much greater than that of the axial walls 26, 28.
  • a bearing washer 50 can be interposed between the clamping nut 46 and the sliding bushing 48 so that the clearance J is provided between facing faces of such a support washer 50 and the flange of FIG. corresponding attachment 34.
  • the presence of a support washer 50 is however not essential but improves the support in operation.
  • each attachment flange 34 is slidable on the corresponding sleeve 48 between a position called “in cold operation” and a position called “in hot operation”.
  • the attachment flanges 34 are mounted prestressed bearing against a shoulder 48a of the slide sleeve 48 to provide the chamber bottom a certain stiffness for dynamic stability.
  • the cold operating phase (FIG. 3A), that is to say the operating phase during which the expansion gap between the chamber bottom 30 and the axial walls 26, 28 is not sufficient to cancel the preload mounting flanges 34, they remain in abutment against the shoulder 48a.
  • the clearance J and the prestressing on mounting of the attachment flanges 34 are therefore dimensioned so as to allow the flanges to abut against the shoulder 48a of the sliding sleeve 48 and against the bearing washer 50 following the phase of operation of the turbomachine.
  • the height of the radial clearance J is thus defined in order to obtain a tension on the fastening flanges 34 necessary for the vibratory stability of the chamber bottom 30.
  • each attachment flange 34 comprises a washer 52 made of metallic material which is traversed by the fixing screw 40 and the corresponding sliding bushing 48, the latter also being made of metallic material. This feature makes it possible to achieve a metal / metal contact between the bushing 48 and the fastening flange 34 which causes much less wear than a ceramic / metal type contact.
  • the metal washer 52 can be advantageously welded to the corresponding fastening flange 34, which facilitates its replacement in case of significant wear.
  • the contact between the metal washer 52 of the attachment flanges 34 and the corresponding sliding sleeve 34 is substantially toroidal.
  • the orifice 42 formed by the metal washer 52 of the fastening flange 34 has a substantially toric shape. This feature has the advantage of facilitating the sliding between the sleeve 48 and the attachment flange 34 by limiting the jamming phenomena.
  • the metal washer 52 of the attachment flanges 34 has an extra thickness relative to the flanges which is intended to increase the contact surface between the washer and the corresponding sliding bushing 48 in order to decrease the wear of the contact between these two elements.
  • the presence of the shoulder 48a of the sliding sleeve 48 makes it possible, on the one hand, to also increase the distribution of the contact forces between the bushing 48 and the attachment flange 34 (and thus to reduce the wear), and secondly to ensure a metal / metal contact with the metal washer 52 of the attachment flanges.
  • the fastening systems 36 may also comprise means for damping vibrations over the entire operating phase of the motor while keeping the radial expansion of the chamber bottom 30 free from the axial walls. , 28.
  • these damping means consist, for each fastening system 36, of a spiral spring 54 which is arranged around the slide sleeve 48 and between the bearing washer 50 (or the clamping nut 46 if it is not present) and the metal washer 52 of the corresponding fastening flange 34, that is to say at the radial clearance J.
  • these damping means consist, for each fastening system 36, of a leaf spring 56 which is also arranged around the slide sleeve 48 and between the spring washer support 50 and the metal washer 52 of the corresponding fastening flange 34, that is to say at the radial clearance J.
  • means for sealing between the chamber bottom 30 and the axial walls 26, 28 may also be provided. As shown in the figures, such means are, for each fastening system 36, in the form of a circular seal 58 of lamella type mounted in an annular groove 60 formed between the fastening flange 34 and the part d upstream end of the corresponding axial wall 26, 28.
  • This seal 58 comprises a spoiler 62 intended to provide an O-bearing on the wall facing the end portion of the axial wall 26, 28.
  • the seal is pressed against the wall by a resilient element 64 of the spring type. with blades, and held in position by a plurality of pins 66 integral with the attachment flanges 34.
  • the seal 58 is confined to the chamber bottom 30 and therefore does not interfere with the flow of air flowing in the annular channel 24.
  • the combustion chamber according to the invention may also comprise an inner cap (or fairing) 68 and an outer cap (or fairing) 70 which are made of the same material as the axial walls 26, 28 of the combustion chamber (c '). that is to say here in composite material) and which extend upstream the end portion of the respective axial walls 26, 28.
  • each screw 40 of the fastening systems 36 also passes through an orifice 72 formed in the corresponding cap 68, 70.
  • the caps can be either directly integrated with the axial walls 26, 28 of the chamber (this is the case of the outer cap 70 of FIG. 1), or distinct from these axial walls (this is the case of the inner cap 68).
  • the combination of fastening flanges with fixing systems having a radial clearance determined according to the invention has many advantages.
  • the attachment flanges allow by their flexibility to damp the vibrations experienced by the combustion chamber and the presence of a radial clearance in the fastening systems allows the flanges to slide in operation, which greatly reduces the constraints flexion to which they are subjected.
  • the use of flexible gripping flanges with a suitable mounting preload thus avoids degrading the integrity of the composite material forming the axial walls of the combustion chamber.
  • the sliding contact between the sleeve and the attachment flange is made between metal parts which limits the damage. In case of wear, the repair of these parts is also simplified since it only requires a simple change of the metal washer of the attachment flanges.
  • the solution of the present invention provides a significant gain in mass.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Connection Of Plates (AREA)
  • Portable Nailing Machines And Staplers (AREA)

Abstract

The chamber has external and internal axial walls connected to a chamber dome (30) having a thermal expansion co-efficient different from that of the axial walls. The dome is connected to internal and external fixing flanges (34). Fixation systems (36) fix the flanges (34) on the walls, respectively. Each fixation system has a sliding bush disposed between a nut (46) and the ends of the walls. A radial gap is provided between the nut and the ends of the walls. The flange (34) has a washer (52) crossed by a clamping bolt (40) and a bush, where the washer and bush are made of metallic materials.

Description

Arrière-plan de l'inventionBackground of the invention

La présente invention se rapporte au domaine général des chambres de combustion de turbomachine. Elle vise plus particulièrement le problème que pose l'assemblage d'une chambre de combustion annulaire dont les parois axiales et le fond de chambre sont réalisés dans des matériaux ayant des coefficients de dilatation thermique différents.The present invention relates to the general field of turbomachine combustion chambers. It relates more particularly to the problem of assembling an annular combustion chamber whose axial walls and the chamber bottom are made of materials having different coefficients of thermal expansion.

Dans le domaine aéronautique, il devient de plus en plus fréquent d'utiliser des matériaux composites haute température de type CMC en remplacement des matériaux métalliques pour réaliser les différents composants d'une turbomachine, notamment la chambre de combustion de celle-ci. L'emploi d'une chambre de combustion entièrement métallique s'avère en effet totalement inadapté d'un point de vue thermique en raison des températures hautement élevées des gaz de combustion. Il en résulte une diminution de la durée de vie de la chambre de combustion.In the aeronautical field, it is becoming increasingly common to use CMC type high temperature composite materials to replace metallic materials to achieve the various components of a turbomachine, including the combustion chamber thereof. The use of an all-metal combustion chamber is indeed totally unsuitable from a thermal point of view because of the high temperatures of the combustion gases. This results in a decrease in the life of the combustion chamber.

Cependant, les matériaux composites sont très coûteux et présentent une résistance assez faible aux fortes sollicitations mécaniques. Aussi, leur utilisation est le plus souvent limitée aux seules parois axiales de la chambre de combustion, la paroi radiale (ou fond de chambre) réunissant en amont ces parois axiales restant alors réalisée plus classiquement en matériau métallique.However, composite materials are very expensive and have a fairly low resistance to high mechanical stresses. Also, their use is usually limited only to the axial walls of the combustion chamber, the radial wall (or chamber bottom) bringing upstream these axial walls remaining then more typically made of metallic material.

Or, les matériaux métalliques et les matériaux composites présentent des coefficients de dilatation thermique très différents. Il en résulte des problèmes au niveau des systèmes d'assemblage de la chambre de combustion entre ses parois axiales en matériau composite et le fond de chambre métallique. Notamment, l'utilisation de systèmes de boulonnages classiques n'est plus possible du point de vue de la tenue mécanique des parois.However, metal materials and composite materials have very different coefficients of thermal expansion. This results in problems in the assembly systems of the combustion chamber between its axial walls of composite material and the metal chamber bottom. In particular, the use of conventional bolting systems is no longer possible from the point of view of the mechanical strength of the walls.

Afin de remédier à cet inconvénient, la publication EP 1 479 975 divulgue l'utilisation de brides d'accrochage qui sont solidaires du fond de chambre et par l'intermédiaire desquelles ce dernier est fixé aux parois axiales. Bien que cette solution soit avantageuse, elle présente toujours de nombreux désavantages. Notamment, un tel système d'assemblage ne permet pas d'offrir une dilatation suffisamment libre tout en assurant un amortissement efficace des vibrations subies en fonctionnement par le fond de chambre. De ce fait, les brides d'accrochage subissent en fonctionnement des contraintes de flexion très importantes qui sont particulièrement préjudiciables à la tenue mécanique de l'ensemble et particulièrement à la tenue du composite.In order to remedy this drawback, the publication EP 1 479 975 discloses the use of fastening flanges which are secured to the chamber bottom and through which the latter is attached to the axial walls. Although this solution is advantageous, it still has many disadvantages. In particular, such an assembly system does not not allow to offer a sufficiently free expansion while ensuring effective damping of the vibrations suffered in operation by the chamber bottom. As a result, the fastening flanges undergo in operation very large bending stresses which are particularly detrimental to the mechanical strength of the assembly and particularly to the strength of the composite.

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

La présente invention a donc pour but principal de pallier de tels inconvénients en proposant un système d'assemblage permettant d'obtenir en fonctionnement une libre dilatation du fond de chambre par rapport aux parois axiales tout en assurant un amortissement efficace des vibrations subies par le fond de chambre.The main object of the present invention is therefore to overcome such drawbacks by proposing an assembly system making it possible, in operation, to obtain free expansion of the chamber bottom with respect to the axial walls while ensuring effective damping of the vibrations undergone by the bottom. of room.

A cet effet, il est prévu une chambre de combustion annulaire comportant des parois axiales externe et interne reliées en amont par un fond de chambre ayant un coefficient de dilatation thermique différent de celui des parois axiales, ledit fond de chambre étant muni d'une pluralité de brides d'accrochage internes et externes fixées par des systèmes de fixation respectivement sur des parties d'extrémité amont des parois interne et externe, chaque système de fixation se composant d'une vis traversant l'une des brides d'accrochage et la partie d'extrémité amont de la paroi axiale correspondante, et d'un écrou serré à l'une des extrémités de la vis de fixation, caractérisée en ce que chaque système de fixation comporte en outre une douille de coulissement disposée autour de la vis de fixation entre l'écrou et la partie d'extrémité de la paroi axiale correspondante, un jeu radial déterminé étant prévu entre l'écrou et la partie d'extrémité de la paroi axiale de façon à permettre en fonctionnement une libre dilatation radiale du fond de chambre par rapport aux parois axiales.For this purpose, there is provided an annular combustion chamber having external and internal axial walls connected upstream by a chamber bottom having a coefficient of thermal expansion different from that of the axial walls, said chamber bottom being provided with a plurality internal and external fastening flanges secured by fastening systems respectively to upstream end portions of the inner and outer walls, each fastening system consisting of a screw passing through one of the fastening flanges and the part upstream end of the corresponding axial wall, and a nut tightened at one end of the fixing screw, characterized in that each fastening system further comprises a sliding sleeve disposed around the fixing screw between the nut and the end portion of the corresponding axial wall, a predetermined radial clearance being provided between the nut and the end portion of the axial wall so as to allow in operation free radial expansion of the chamber bottom relative to the axial walls.

La présence des brides d'accrochage souples mais précontraintes combinée à des systèmes de fixation ayant un jeu radial déterminé prévu entre l'écrou et la paroi axiale a pour effet d'améliorer à la fois l'amortissement des vibrations subies par la chambre de combustion et d'atténuer les effets de la dilatation en fonctionnement du fond de chambre par rapport aux parois axiales. De ce fait, les brides d'accrochage ne sont soumises en fonctionnement qu'à de faibles contraintes de flexion.The presence of flexible but prestressed fastening flanges combined with fastening systems having a predetermined radial clearance provided between the nut and the axial wall has the effect of improving both the damping of the vibrations undergone by the combustion chamber. and to mitigate the effects of the expansion in operation of the chamber bottom with respect to the axial walls. As a result, the flanges fastening are subjected in operation to low flexural stresses.

Selon une disposition avantageuse de l'invention, chaque bride d'accrochage comporte une rondelle en matériau métallique qui est traversée par la vis de fixation et la douille de coulissement correspondante, la douille étant réalisée en matériau métallique. Le contact entre la douille et la bride d'accrochage est de type métal/métal. Un tel contact présente l'avantage d'entraîner des usures beaucoup moins importantes et des réparations d'un coût limité par rapport à un contact de type céramique/métal.According to an advantageous arrangement of the invention, each attachment flange comprises a washer made of metallic material which is traversed by the fixing screw and the corresponding sliding bushing, the bushing being made of metallic material. The contact between the bushing and the fastening flange is of metal / metal type. Such contact has the advantage of causing much less wear and repairs of a limited cost compared to a contact of the ceramic / metal type.

Selon une autre disposition avantageuse de l'invention, le contact entre la rondelle des brides d'accrochage et la douille de coulissement correspondante est sensiblement torique. Ce type de contact a pour avantage, en évitant le phénomène de coincement, de faciliter le coulissement entre la douille et la bride d'accrochage.According to another advantageous arrangement of the invention, the contact between the washer of the attachment flanges and the corresponding sliding sleeve is substantially toroidal. This type of contact has the advantage, by avoiding the jamming phenomenon, to facilitate sliding between the bushing and the attachment flange.

Selon encore une autre disposition avantageuse de l'invention, la rondelle des brides d'accrochage présente une surépaisseur destinée à augmenter la hauteur de contact entre la rondelle et la douille de coulissement correspondante. La répartition des forces de contact est ainsi augmentée, ce qui diminue l'usure du contact entre la douille et la bride d'accrochage.According to yet another advantageous arrangement of the invention, the washer of the attachment flanges has an extra thickness intended to increase the height of contact between the washer and the corresponding sliding sleeve. The distribution of the contact forces is thus increased, which reduces the wear of the contact between the bushing and the fastening flange.

De préférence, chaque bride d'accrochage comporte une même précontrainte au montage destinée à apporter au fond de chambre une raideur pour la stabilité dynamique en phase de fonctionnement initial.Preferably, each attachment flange comprises the same preload assembly to provide the chamber bottom stiffness for dynamic stability in the initial operating phase.

Les systèmes de fixation peuvent comporter des moyens pour amortir les vibrations dans la phase de dilatation radiale du fond de chambre par rapport aux parois axiales. De tels moyens peuvent se composer d'un ressort de type à spirale ou à lame disposé autour de la douille de coulissement et entre l'écrou et la bride d'accrochage correspondante.The fastening systems may comprise means for damping the vibrations in the radial expansion phase of the chamber bottom with respect to the axial walls. Such means may consist of a spiral type spring or blade disposed around the slide sleeve and between the nut and the corresponding fastening flange.

Des moyens pour assurer l'étanchéité entre le fond de chambre et les parois axiales peuvent également être prévus. Ces moyens peuvent se composer d'un joint circulaire de type à lamelles monté dans une gorge annulaire formée entre les brides d'accrochage et la partie d'extrémité de la paroi axiale correspondante et comportant un becquet destiné à assurer un appui torique sur la partie d'extrémité de la paroi axiale.Means for sealing between the chamber bottom and the axial walls may also be provided. These means may consist of a lamella-type circular seal mounted in an annular groove formed between the attachment flanges and the end portion of the corresponding axial wall and having a spoiler designed to provide a toric support on the part. end of the axial wall.

Avantageusement, une casquette interne et une casquette externe réalisées en matériau composite prolongent vers l'amont la partie d'extrémité des parois axiales respectives, chaque vis de fixation traversant également un orifice formé dans la casquette correspondante.Advantageously, an inner cap and an outer cap made of composite material extend upstream of the end portion of the respective axial walls, each fastening screw also passing through an orifice formed in the corresponding cap.

La présente invention a également pour objet un système pour la fixation du fond de chambre sur les parois axiales interne et externe d'une chambre de combustion annulaire telle que définie précédemment.The present invention also relates to a system for fixing the chamber bottom to the inner and outer axial walls of an annular combustion chamber as defined above.

Brève description des dessinsBrief description of the drawings

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

  • la figure 1 est une vue partielle et en coupe d'une chambre de combustion de turbomachine selon l'invention ;
  • la figure 2 est une vue partielle et en perspective montrant un système de fixation de la chambre de combustion de la figure 1 ;
  • les figures 3A et 3B sont des vues en coupe montrant en fonctionnement à froid et à chaud un système de fixation de la figure 1 ;
  • les figures 4 et 5 sont des vues en coupe d'un système de fixation de la figure 1 équipé de différents moyens d'amortissement.
Other features and advantages of the present invention will emerge from the description given below, with reference to the accompanying drawings which illustrate an embodiment having no limiting character. In the figures:
  • Figure 1 is a partial sectional view of a turbomachine combustion chamber according to the invention;
  • Figure 2 is a partial perspective view showing a fixing system of the combustion chamber of Figure 1;
  • Figures 3A and 3B are sectional views showing in cold and hot operation a fastening system of Figure 1;
  • Figures 4 and 5 are sectional views of a fastening system of Figure 1 equipped with different damping means.

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

La figure 1 représente partiellement en coupe axiale une chambre de combustion 10 de turbomachine dans son environnement.FIG. 1 partially shows in axial section a combustion chamber 10 of a turbomachine in its environment.

Une enveloppe annulaire externe (ou carter externe) 12 et une enveloppe annulaire interne (ou carter interne) 14 coaxiale à cette dernière sont centrées sur l'axe X-X de la turbomachine. Un espace annulaire 16 formé entre ces deux enveloppes reçoit de l'air comprimé selon un flux général F provenant d'un compresseur (non représenté) de la turbomachine au travers d'un conduit annulaire de diffusion 18. Cet air est destiné à la combustion du carburant dans la chambre 10.An outer annular envelope (or outer casing) 12 and an inner annular envelope (or inner casing) 14 coaxial with the latter are centered on the X-X axis of the turbomachine. An annular space 16 formed between these two envelopes receives compressed air according to a general flow F from a compressor (not shown) of the turbomachine through an annular diffusion duct 18. This air is intended for combustion fuel in the chamber 10.

Une pluralité de systèmes d'injection 20 régulièrement répartis autour du conduit de diffusion 18 débouchent dans l'espace annulaire 16. Ces systèmes d'injection sont chacun munis d'une buse d'injection de carburant 22 fixée sur l'enveloppe externe 12. Dans un souci de simplification des dessins, le mélangeur et le déflecteur associés à chaque buse d'injection n'ont pas été représentés.A plurality of injection systems 20 regularly distributed around the diffusion duct 18 open into the annular space 16. These injection systems are each provided with a fuel injection nozzle 22 fixed to the outer casing 12. In order to simplification of the drawings, the mixer and the baffle associated with each injection nozzle have not been represented.

La chambre de combustion 10 de la turbomachine est montée à l'intérieur de cet espace annulaire 16 en ménageant avec les enveloppes externe 12 et interne 14 un canal annulaire 24 destiné à recevoir un débit d'air de dilution et de refroidissement. Cette chambre est de type annulaire ; elle est formée d'une paroi axiale externe 26 et d'une paroi axiale interne 28 coaxiale à cette dernière. Ces parois axiales 26, 28 sont centrées sur l'axe X-X de la turbomachine.The combustion chamber 10 of the turbomachine is mounted within this annular space 16 by providing with the outer casings 12 and inner 14 an annular channel 24 for receiving a flow of dilution and cooling air. This chamber is of annular type; it is formed of an outer axial wall 26 and an inner axial wall 28 coaxial with the latter. These axial walls 26, 28 are centered on the X-X axis of the turbomachine.

Une paroi transversale 30 formant fond de chambre relie en amont les parois axiales 26, 28 de la chambre de combustion. Ce fond de chambre 30 est pourvu d'une pluralité d'ouvertures 32 pour le passage des buses d'injection de carburant 22.A transverse wall 30 forming a chamber bottom connects upstream the axial walls 26, 28 of the combustion chamber. This chamber bottom 30 is provided with a plurality of openings 32 for the passage of the fuel injection nozzles 22.

Le fond de chambre 30 et les parois axiales 26, 28 sont réalisées dans des matériaux ayant des coefficients de dilatation thermique très différents. Par exemple, les parois axiales peuvent être réalisées en matériau céramique haute température de type CMC ou autres, tandis que le fond de chambre peut être réalisé en matériau métallique.The chamber bottom 30 and the axial walls 26, 28 are made of materials having very different thermal expansion coefficients. For example, the axial walls may be made of high temperature ceramic material CMC type or other, while the chamber bottom may be made of metal material.

Comme représenté sur les figures 1 et 2, le fond de chambre 30 est muni à ses extrémités d'une pluralité de brides d'accrochage souples internes et externes 34 qui sont chacune fixées sur les parties d'extrémité amont des parois axiales 26, 28 au moyen d'un système de fixation 36 de type boulonnage.As shown in FIGS. 1 and 2, the chamber bottom 30 is provided at its ends with a plurality of internal and external flexible hooking flanges 34 which are each attached to the upstream end portions of the axial walls 26, 28. by means of a fixing system 36 of the bolting type.

Les brides d'accrochage 34 se présentent sous la forme de languettes souples qui sont intégrées dans des anneaux respectifs 38 rendus solidaires du fond de chambre 30, par exemple par soudage. Elles s'étendent vers l'amont au-delà des systèmes de fixation 36 et sont régulièrement réparties sur toute la circonférence de la chambre de combustion.The attachment flanges 34 are in the form of flexible tongues which are integrated in respective rings 38 secured to the chamber bottom 30, for example by welding. They extend upstream beyond the fastening systems 36 and are regularly distributed over the entire circumference of the combustion chamber.

Comme représenté sur les figures 3A et 3B, les systèmes de fixation 36 se composent chacun d'une vis de fixation 40 traversant des orifices 42, 44 formés respectivement dans la bride d'accrochage correspondante 34 et dans la partie d'extrémité amont de la paroi axiale correspondante 26, 28. Un écrou 46 est serré à l'une des extrémités de la vis de fixation 40.As shown in FIGS. 3A and 3B, the fixing systems 36 each consist of a fastening screw 40 passing through orifices 42, 44 respectively formed in the corresponding fastening flange 34 and in the upstream end portion of the corresponding axial wall 26, 28. A nut 46 is tightened at one end of the fixing screw 40.

Selon l'invention, chaque système de fixation 36 comporte en outre une douille de coulissement 48 disposée autour de la vis de fixation 40 entre l'écrou de serrage 46 et la partie d'extrémité amont de la paroi axiale correspondante 26, 28 de la chambre de combustion. Par ailleurs, un jeu radial J déterminé est prévu entre l'écrou 46 et la partie d'extrémité amont de la paroi axiale 26, 28. Ainsi, la douille de coulissement 48 présente une hauteur radiale suffisante pour ménager un tel jeu J. According to the invention, each fastening system 36 further comprises a sliding sleeve 48 disposed around the fastening screw 40 between the clamping nut 46 and the upstream end portion of the corresponding axial wall 26, 28 of the combustion chamber. Furthermore, a determined radial clearance J is provided between the nut 46 and the upstream end portion of the axial wall 26, 28. Thus, the sliding sleeve 48 has a radial height sufficient to provide such clearance J.

Le jeu J prévu au niveau de chaque système de fixation 36 de la chambre de combustion permet en fonctionnement d'obtenir une libre dilatation radiale du fond de chambre 30 par rapport aux parois axiales 26, 28. Une telle dilatation est rendue nécessaire par le fait que le fond de chambre 30 présente un coefficient de dilatation thermique très supérieur à celui des parois axiales 26, 28.The clearance J provided at each attachment system 36 of the combustion chamber in operation makes it possible to obtain radial free expansion of the chamber bottom 30 with respect to the axial walls 26, 28. Such an expansion is made necessary by the fact that that the chamber bottom 30 has a coefficient of thermal expansion much greater than that of the axial walls 26, 28.

Une rondelle d'appui 50 peut être intercalée entre l'écrou de serrage 46 et la douille de coulissement 48 de sorte que le jeu J est prévu entre des faces en regard d'une telle rondelle d'appui 50 et de la bride d'accrochage correspondante 34. La présence d'une rondelle d'appui 50 n'est cependant pas indispensable mais améliore l'appui en fonctionnement.A bearing washer 50 can be interposed between the clamping nut 46 and the sliding bushing 48 so that the clearance J is provided between facing faces of such a support washer 50 and the flange of FIG. corresponding attachment 34. The presence of a support washer 50 is however not essential but improves the support in operation.

Avec une telle configuration, chaque bride d'accrochage 34 est apte à coulisser sur la douille 48 correspondante entre une position dite « en fonctionnement à froid » et une position dite « en fonctionnement à chaud ».With such a configuration, each attachment flange 34 is slidable on the corresponding sleeve 48 between a position called "in cold operation" and a position called "in hot operation".

Lors de l'assemblage de la chambre de combustion, les brides d'accrochage 34 sont montées précontraintes en appui contre un épaulement 48a de la douille de coulissement 48 afin d'apporter au fond de chambre une certaine raideur pour la stabilité dynamique. Dans la phase de fonctionnement à froid (figure 3A), c'est-à-dire la phase de fonctionnement pendant laquelle l'écart de dilatation entre le fond de chambre 30 et les parois axiales 26, 28 n'est pas suffisant pour annuler la précontrainte de montage des brides d'accrochage 34, celles-ci restent en appui contre l'épaulement 48a.During assembly of the combustion chamber, the attachment flanges 34 are mounted prestressed bearing against a shoulder 48a of the slide sleeve 48 to provide the chamber bottom a certain stiffness for dynamic stability. In the cold operating phase (FIG. 3A), that is to say the operating phase during which the expansion gap between the chamber bottom 30 and the axial walls 26, 28 is not sufficient to cancel the preload mounting mounting flanges 34, they remain in abutment against the shoulder 48a.

Dans la phase de fonctionnement à chaud (figure 3B), c'est-à-dire la phase de fonctionnement pendant laquelle l'écart de dilatation entre le fond de chambre 30 et les parois axiales 26, 28 compense la précontrainte de montage des brides d'accrochage 34, celles-ci coulissent chacune radialement le long de la douille correspondante 48 pour venir en butée contre la rondelle d'appui 50 (ou contre l'écrou de serrage 46 si cette rondelle n'est pas présente).In the hot running phase (FIG. 3B), that is to say the operating phase during which the expansion gap between the chamber bottom 30 and the axial walls 26, 28 compensates for the flange mounting preload latch 34, these slide each radially along the corresponding sleeve 48 to abut against the bearing washer 50 (or against the clamping nut 46 if this washer is not present).

Le jeu J et la précontrainte au montage des brides d'accrochage 34 sont donc dimensionnés de façon à permettre une mise en butée des brides contre l'épaulement 48a de la douille de coulissement 48 et contre la rondelle d'appui 50 suivant la phase de fonctionnement de la turbomachine. La hauteur du jeu radial J est ainsi définie afin d'obtenir une tension sur les brides d'accrochage 34 nécessaire à la stabilité vibratoire du fond de chambre 30.The clearance J and the prestressing on mounting of the attachment flanges 34 are therefore dimensioned so as to allow the flanges to abut against the shoulder 48a of the sliding sleeve 48 and against the bearing washer 50 following the phase of operation of the turbomachine. The height of the radial clearance J is thus defined in order to obtain a tension on the fastening flanges 34 necessary for the vibratory stability of the chamber bottom 30.

Selon une caractéristique avantageuse de l'invention, chaque bride d'accrochage 34 comporte une rondelle 52 en matériau métallique qui est traversée par la vis de fixation 40 et la douille de coulissement correspondante 48, cette dernière étant également réalisée en matériau métallique. Cette caractéristique permet de réaliser un contact métal/métal entre la douille 48 et la bride d'accrochage 34 qui occasionne une usure beaucoup moins importante qu'un contact de type céramique/métal.According to an advantageous characteristic of the invention, each attachment flange 34 comprises a washer 52 made of metallic material which is traversed by the fixing screw 40 and the corresponding sliding bushing 48, the latter also being made of metallic material. This feature makes it possible to achieve a metal / metal contact between the bushing 48 and the fastening flange 34 which causes much less wear than a ceramic / metal type contact.

Par ailleurs, la rondelle métallique 52 peut être avantageusement soudée à la bride d'accrochage correspondante 34, ce qui facilite son remplacement en cas d'usure importante.Furthermore, the metal washer 52 can be advantageously welded to the corresponding fastening flange 34, which facilitates its replacement in case of significant wear.

Selon une autre caractéristique avantageuse de l'invention, le contact entre la rondelle métallique 52 des brides d'accrochage 34 et la douille de coulissement correspondante 34 est sensiblement torique. A cet effet, comme représenté sur les figures 3A et 3B, l'orifice 42 formé par la rondelle métallique 52 de la bride d'accrochage 34 a une forme sensiblement torique. Cette caractéristique a pour avantage de faciliter le coulissement entre la douille 48 et la bride d'accrochage 34 en limitant les phénomènes de coincement.According to another advantageous characteristic of the invention, the contact between the metal washer 52 of the attachment flanges 34 and the corresponding sliding sleeve 34 is substantially toroidal. For this purpose, as shown in Figures 3A and 3B, the orifice 42 formed by the metal washer 52 of the fastening flange 34 has a substantially toric shape. This feature has the advantage of facilitating the sliding between the sleeve 48 and the attachment flange 34 by limiting the jamming phenomena.

Selon encore une autre caractéristique avantageuse de l'invention, la rondelle métallique 52 des brides d'accrochage 34 présente une surépaisseur par rapport aux brides qui est destinée à augmenter la surface de contact entre la rondelle et la douille de coulissement correspondante 48 afin de diminuer l'usure du contact entre ces deux éléments.According to yet another advantageous characteristic of the invention, the metal washer 52 of the attachment flanges 34 has an extra thickness relative to the flanges which is intended to increase the contact surface between the washer and the corresponding sliding bushing 48 in order to decrease the wear of the contact between these two elements.

On notera que la présence de l'épaulement 48a de la douille de coulissement 48 permet, d'une part d'augmenter également la répartition des forces de contact entre la douille 48 et la bride d'accrochage 34 (et donc de diminuer l'usure), et d'autre part d'assurer un contact métal/métal avec la rondelle métallique 52 des brides d'accrochage.It will be noted that the presence of the shoulder 48a of the sliding sleeve 48 makes it possible, on the one hand, to also increase the distribution of the contact forces between the bushing 48 and the attachment flange 34 (and thus to reduce the wear), and secondly to ensure a metal / metal contact with the metal washer 52 of the attachment flanges.

Comme représenté sur les figures 4 et 5, les systèmes de fixation 36 peuvent également comporter des moyens pour amortir des vibrations sur toute la phase de fonctionnement du moteur en gardant « libre » la dilatation radiale du fond de chambre 30 par rapport aux parois axiales 26, 28.As shown in FIGS. 4 and 5, the fastening systems 36 may also comprise means for damping vibrations over the entire operating phase of the motor while keeping the radial expansion of the chamber bottom 30 free from the axial walls. , 28.

Sur l'exemple de réalisation de la figure 4, ces moyens d'amortissement se composent, pour chaque système de fixation 36, d'un ressort à spirale 54 qui est disposé autour de la douille de coulissement 48 et entre la rondelle d'appui 50 (ou l'écrou de serrage 46 si celle-ci n'est pas présente) et la rondelle métallique 52 de la bride d'accrochage correspondante 34, c'est-à-dire au niveau du jeu radial J. In the exemplary embodiment of FIG. 4, these damping means consist, for each fastening system 36, of a spiral spring 54 which is arranged around the slide sleeve 48 and between the bearing washer 50 (or the clamping nut 46 if it is not present) and the metal washer 52 of the corresponding fastening flange 34, that is to say at the radial clearance J.

Selon un autre exemple de réalisation illustré par la figure 5, ces moyens d'amortissement se composent, pour chaque système de fixation 36, d'un ressort à lame 56 qui est également disposé autour de la douille de coulissement 48 et entre la rondelle d'appui 50 et la rondelle métallique 52 de la bride d'accrochage correspondante 34, c'est-à-dire au niveau du jeu radial J.According to another exemplary embodiment illustrated in FIG. 5, these damping means consist, for each fastening system 36, of a leaf spring 56 which is also arranged around the slide sleeve 48 and between the spring washer support 50 and the metal washer 52 of the corresponding fastening flange 34, that is to say at the radial clearance J.

Par ailleurs, des moyens pour assurer l'étanchéité entre le fond de chambre 30 et les parois axiales 26, 28 peuvent aussi être prévus. Comme représenté sur les figures, de tels moyens se présentent, pour chaque système de fixation 36, sous la forme d'un joint circulaire 58 de type à lamelles monté dans une gorge annulaire 60 formée entre la bride d'accrochage 34 et la partie d'extrémité amont de la paroi axiale correspondante 26, 28.Furthermore, means for sealing between the chamber bottom 30 and the axial walls 26, 28 may also be provided. As shown in the figures, such means are, for each fastening system 36, in the form of a circular seal 58 of lamella type mounted in an annular groove 60 formed between the fastening flange 34 and the part d upstream end of the corresponding axial wall 26, 28.

Ce joint d'étanchéité 58 comporte un becquet 62 destiné à assurer un appui torique sur la paroi en regard de la partie d'extrémité de la paroi axiale 26, 28. Le joint est plaqué contre la paroi par un élément élastique 64 de type ressort à lames, et maintenu en position par une pluralité de pions 66 solidaires des brides d'accrochage 34.This seal 58 comprises a spoiler 62 intended to provide an O-bearing on the wall facing the end portion of the axial wall 26, 28. The seal is pressed against the wall by a resilient element 64 of the spring type. with blades, and held in position by a plurality of pins 66 integral with the attachment flanges 34.

Avec une telle configuration, le joint d'étanchéité 58 est confiné vers le fond de chambre 30 et ne gêne donc pas l'écoulement de l'air circulant dans le canal annulaire 24.With such a configuration, the seal 58 is confined to the chamber bottom 30 and therefore does not interfere with the flow of air flowing in the annular channel 24.

La chambre de combustion selon l'invention peut également comporter une casquette (ou carénage) interne 68 et une casquette (ou carénage) externe 70 qui sont réalisées dans le même matériau que les parois axiales 26, 28 de la chambre de combustion (c'est-à-dire ici en matériau composite) et qui prolongent vers l'amont la partie d'extrémité des parois axiales 26, 28 respectives. Dans ce cas, chaque vis 40 des systèmes de fixation 36 traverse également un orifice 72 formé dans la casquette 68, 70 correspondante.The combustion chamber according to the invention may also comprise an inner cap (or fairing) 68 and an outer cap (or fairing) 70 which are made of the same material as the axial walls 26, 28 of the combustion chamber (c '). that is to say here in composite material) and which extend upstream the end portion of the respective axial walls 26, 28. In this case, each screw 40 of the fastening systems 36 also passes through an orifice 72 formed in the corresponding cap 68, 70.

Comme représenté sur la figure 1, les casquettes peuvent être soit directement intégrées aux parois axiales 26, 28 de la chambre (c'est le cas de la casquette externe 70 de la figure 1), soit distinctes de ces parois axiales (c'est le cas de la casquette interne 68).As shown in FIG. 1, the caps can be either directly integrated with the axial walls 26, 28 of the chamber (this is the case of the outer cap 70 of FIG. 1), or distinct from these axial walls (this is the case of the inner cap 68).

L'association de brides d'accrochage avec des systèmes de fixation ayant un jeu radial déterminé selon l'invention présente de nombreux avantages. Notamment, les brides d'accrochage permettent par leur souplesse d'amortir les vibrations subies par la chambre de combustion et la présence d'un jeu radial au niveau des systèmes de fixation permet aux brides de coulisser en fonctionnement, ce qui diminue fortement les contraintes de flexion auxquelles elles sont soumises. L'utilisation des brides d'accrochage souples avec une précontrainte au montage adaptée évite ainsi de dégrader l'intégrité du matériau composite formant les parois axiales de la chambre de combustion. Par ailleurs, le contact de coulissement entre la douille et la bride d'accrochage est réalisé entre des pièces métalliques ce qui limite les dégradations. En cas d'usure, la réparation de ces pièces est également simplifiée puisqu'elle ne nécessite qu'un simple changement de la rondelle métallique des brides d'accrochage. Enfin, par rapport aux systèmes connus de l'art antérieur, la solution de la présente invention apporte un gain de masse significatif.The combination of fastening flanges with fixing systems having a radial clearance determined according to the invention has many advantages. In particular, the attachment flanges allow by their flexibility to damp the vibrations experienced by the combustion chamber and the presence of a radial clearance in the fastening systems allows the flanges to slide in operation, which greatly reduces the constraints flexion to which they are subjected. The use of flexible gripping flanges with a suitable mounting preload thus avoids degrading the integrity of the composite material forming the axial walls of the combustion chamber. Furthermore, the sliding contact between the sleeve and the attachment flange is made between metal parts which limits the damage. In case of wear, the repair of these parts is also simplified since it only requires a simple change of the metal washer of the attachment flanges. Finally, compared to known systems of the prior art, the solution of the present invention provides a significant gain in mass.

Claims (10)

Chambre de combustion annulaire (10) comportant des parois axiales externe (26) et interne (28) reliées en amont par un fond de chambre (30) ayant un coefficient de dilatation thermique différent de celui desdites parois axiales (26, 28), ledit fond de chambre (30) étant muni d'une pluralité de brides d'accrochage (34) internes et externes fixées par des systèmes de fixation (36) respectivement sur des parties d'extrémité amont des parois interne et externe (26, 28), chaque système de fixation (36) se composant d'une vis (40) traversant l'une des brides d'accrochage (34) et la partie d'extrémité amont de la paroi axiale correspondante (26, 28), et d'un écrou (46) serré à l'une des extrémités de la vis de fixation, caractérisée en ce que chaque système de fixation (36) comporte en outre une douille de coulissement (48) disposée autour de la vis de fixation (40) entre l'écrou (46) et la partie d'extrémité de la paroi axiale correspondante (26, 28), un jeu radial (J) déterminé étant prévu entre l'écrou et la partie d'extrémité de la paroi axiale de façon à permettre en fonctionnement une libre dilatation radiale du fond de chambre (30) par rapport aux parois axiales (26, 28).An annular combustion chamber (10) having outer (26) and inner (28) axial walls connected upstream by a chamber bottom (30) having a coefficient of thermal expansion different from that of said axial walls (26, 28), said chamber base (30) being provided with a plurality of internal and external attachment flanges (34) secured by fastening systems (36) respectively to upstream end portions of the inner and outer walls (26, 28) , each fastening system (36) consisting of a screw (40) passing through one of the attachment flanges (34) and the upstream end portion of the corresponding axial wall (26, 28), and a nut (46) tightened at one end of the fixing screw, characterized in that each fastening system (36) further comprises a sliding sleeve (48) disposed around the fastening screw (40) between the nut (46) and the end portion of the corresponding axial wall (26, 28), a radial clearance ( J ) being provided between the nut and the end portion of the axial wall so as to allow in operation radial free expansion of the chamber bottom (30) relative to the axial walls (26, 28). Chambre de combustion selon la revendication 1, dans laquelle chaque bride d'accrochage (34) comporte une rondelle (52) en matériau métallique qui est traversée par la vis de fixation (40) et la douille de coulissement (48) correspondante, la douille (48) étant réalisée en matériau métallique.Combustion chamber according to claim 1, wherein each fastening flange (34) comprises a washer (52) of metal material which is traversed by the fixing screw (40) and the corresponding sliding bushing (48), the bushing (48) being made of metallic material. Chambre de combustion selon la revendication 2, dans laquelle le contact entre la rondelle (52) des brides d'accrochage (34) et la douille de coulissement (48) correspondante est sensiblement torique.Combustion chamber according to claim 2, wherein the contact between the washer (52) of the attachment flanges (34) and the corresponding sliding bushing (48) is substantially toroidal. Chambre de combustion selon l'une des revendications 2 et 3, dans laquelle la rondelle (52) des brides d'accrochage (34) présente une surépaisseur destinée à augmenter la surface de contact entre ladite rondelle et la douille de coulissement (48) correspondante.Combustion chamber according to one of claims 2 and 3, wherein the washer (52) of the attachment flanges (34) has an extra thickness to increase the contact surface between said washer and the sliding sleeve (48) corresponding . Chambre de combustion selon l'une quelconque des revendications 1 à 4, dans laquelle chaque bride d'accrochage (34) comporte une précontrainte au montage destinée à apporter au fond de chambre (10) une raideur pour la stabilité dynamique.Combustion chamber according to any one of claims 1 to 4, wherein each attachment flange (34) comprises an assembly preload intended to provide the chamber bottom (10) a stiffness for dynamic stability. Chambre de combustion selon l'une quelconque des revendications 1 à 5, dans laquelle les systèmes de fixation (36) comportent en outre des moyens (54, 56) pour amortir des vibrations du fond de chambre (30) par rapport aux parois axiales (26, 28).Combustion chamber according to any one of claims 1 to 5, wherein the fastening systems (36) further comprise means (54, 56) for damping vibrations of the chamber base (30) with respect to the axial walls ( 26, 28). Chambre de combustion selon la revendication 6, dans laquelle les moyens d'amortissement se composent d'un ressort de type à spirale (54) ou à lame (56) disposé autour de la douille de coulissement (48) et entre l'écrou (46) et la bride d'accrochage (34) correspondante.Combustion chamber according to Claim 6, in which the damping means consist of a spiral (54) or leaf spring (56) arranged around the slide sleeve (48) and between the nut ( 46) and the corresponding attachment flange (34). Chambre de combustion selon l'une quelconque des revendications 1 à 7, comportant en outre des moyens (58, 62) pour assurer l'étanchéité entre le fond de chambre (30) et les parois axiales (26, 28).Combustion chamber according to any one of claims 1 to 7, further comprising means (58, 62) for sealing between the chamber bottom (30) and the axial walls (26, 28). Chambre de combustion selon la revendication 8, dans laquelle les moyens d'étanchéité se composent d'un joint circulaire (58) de type à lamelles monté dans une gorge annulaire (60) formée entre les brides d'accrochage (34) et la partie d'extrémité de la paroi axiale correspondante (26, 28) et comportant un becquet (62) destiné à assurer un appui torique sur ladite partie d'extrémité de la paroi axiale.Combustion chamber according to claim 8, wherein the sealing means consist of a lamella-type circular seal (58) mounted in an annular groove (60) formed between the attachment flanges (34) and the portion end of the corresponding axial wall (26, 28) and having a spoiler (62) for providing an O-bearing on said end portion of the axial wall. Chambre de combustion selon l'une quelconque des revendications 1 à 9, comportant en outre une casquette interne (68) et une casquette externe (70) qui prolongent vers l'amont la partie d'extrémité des parois axiales respectives (26, 28), chaque vis de fixation (36) traversant également un orifice (72) formé dans la casquette correspondante.Combustion chamber according to any one of claims 1 to 9, further comprising an inner cap (68) and an outer cap (70) which extend upstream the end portion of the respective axial walls (26, 28) each fixing screw (36) also passing through an orifice (72) formed in the corresponding cap.
EP06114424.2A 2005-06-14 2006-05-23 Assembly of an annular combustion chamber for a turbine Active EP1734305B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0505999A FR2887015B1 (en) 2005-06-14 2005-06-14 ASSEMBLY OF AN ANNULAR COMBUSTION CHAMBER OF TURBOMACHINE

Publications (3)

Publication Number Publication Date
EP1734305A2 true EP1734305A2 (en) 2006-12-20
EP1734305A3 EP1734305A3 (en) 2013-05-01
EP1734305B1 EP1734305B1 (en) 2014-07-02

Family

ID=34955491

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06114424.2A Active EP1734305B1 (en) 2005-06-14 2006-05-23 Assembly of an annular combustion chamber for a turbine

Country Status (6)

Country Link
US (1) US7849696B2 (en)
EP (1) EP1734305B1 (en)
JP (1) JP2006349336A (en)
CA (1) CA2548905C (en)
FR (1) FR2887015B1 (en)
RU (1) RU2400674C2 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3056665A1 (en) * 2014-12-05 2016-08-17 Rolls-Royce Corporation Gas turbine engine and process of coupling a first to a second component in a gas turbine engine
EP3211311B1 (en) * 2016-02-25 2020-07-22 General Electric Company Combuster assembly

Families Citing this family (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7874059B2 (en) * 2006-01-12 2011-01-25 Siemens Energy, Inc. Attachment for ceramic matrix composite component
FR2911668B1 (en) 2007-01-18 2009-03-20 Snecma Sa COMBUSTION CHAMBER OF A TURBOMACHINE
GB2453946B (en) * 2007-10-23 2010-07-14 Rolls Royce Plc A Wall Element for use in Combustion Apparatus
GB0800294D0 (en) * 2008-01-09 2008-02-20 Rolls Royce Plc Gas heater
GB0801839D0 (en) * 2008-02-01 2008-03-05 Rolls Royce Plc combustion apparatus
GB2457281B (en) * 2008-02-11 2010-09-08 Rolls Royce Plc A Combustor Wall Arrangement with Parts Joined by Mechanical Fasteners
GB2460634B (en) * 2008-06-02 2010-07-07 Rolls Royce Plc Combustion apparatus
FR2935753B1 (en) * 2008-09-08 2011-07-01 Snecma Propulsion Solide FASTENING, FASTENING CONNECTIONS FOR MOUNTING CMC PIECES
GB0920371D0 (en) * 2009-11-23 2010-01-06 Rolls Royce Plc Combustor system
US8607577B2 (en) * 2009-11-24 2013-12-17 United Technologies Corporation Attaching ceramic matrix composite to high temperature gas turbine structure
US9322334B2 (en) * 2012-10-23 2016-04-26 General Electric Company Deformable mounting assembly
FR2998038B1 (en) 2012-11-09 2017-12-08 Snecma COMBUSTION CHAMBER FOR A TURBOMACHINE
WO2015017180A1 (en) * 2013-08-01 2015-02-05 United Technologies Corporation Attachment scheme for a ceramic bulkhead panel
US10012104B2 (en) 2014-10-14 2018-07-03 United Technologies Corporation Gas turbine engine convergent/divergent nozzle with unitary synchronization ring for roller track nozzle
US10197278B2 (en) 2015-09-02 2019-02-05 General Electric Company Combustor assembly for a turbine engine
US9976746B2 (en) 2015-09-02 2018-05-22 General Electric Company Combustor assembly for a turbine engine
US11149646B2 (en) 2015-09-02 2021-10-19 General Electric Company Piston ring assembly for a turbine engine
US10168051B2 (en) * 2015-09-02 2019-01-01 General Electric Company Combustor assembly for a turbine engine
US9951649B2 (en) 2016-04-26 2018-04-24 Pratt & Whitney Canada Corp. Fuel flow divider valve mounting arrangement for a gas turbine engine
US10935242B2 (en) * 2016-07-07 2021-03-02 General Electric Company Combustor assembly for a turbine engine
US10280959B2 (en) 2016-07-13 2019-05-07 Rohr, Inc. Sliding fastener systems to accommodate differential thermal growth
GB201613110D0 (en) 2016-07-29 2016-09-14 Rolls Royce Plc A combustion chamber
US20180051880A1 (en) * 2016-08-18 2018-02-22 General Electric Company Combustor assembly for a turbine engine
US10385709B2 (en) * 2017-02-23 2019-08-20 General Electric Company Methods and features for positioning a flow path assembly within a gas turbine engine
US11402097B2 (en) 2018-01-03 2022-08-02 General Electric Company Combustor assembly for a turbine engine
US11054136B2 (en) * 2018-11-30 2021-07-06 Pratt & Whitney Canada Corp. Interface for double-skin combustor liner
US11378012B2 (en) * 2019-12-12 2022-07-05 Rolls-Royce Plc Insert-mounted turbine assembly for a gas turbine engine
US11525577B2 (en) * 2020-04-27 2022-12-13 Raytheon Technologies Corporation Extended bulkhead panel
EP3929487B1 (en) * 2020-06-25 2024-08-07 General Electric Company Combustor assembly for a gas turbine engine
CN113931872B (en) * 2021-12-15 2022-03-18 成都中科翼能科技有限公司 Double-layer drum barrel reinforced rotor structure of gas compressor of gas turbine
CN116697399A (en) * 2022-02-28 2023-09-05 通用电气公司 Combustor dome-baffle and liner with flexible connection
CN116928696A (en) 2022-03-31 2023-10-24 通用电气公司 Liner assembly for a combustor

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1265031A1 (en) * 2001-06-06 2002-12-11 Snecma Moteurs Fixing of metallic cowls on turbomachine combustion chamber liners made of CMC materials
EP1265033A1 (en) * 2001-06-06 2002-12-11 Snecma Moteurs Combustion chamber with a system for mounting the chamber end wall
EP1431665A2 (en) * 2002-12-20 2004-06-23 General Electric Company Mounting assembly for the forward end of a ceramic matrix composite liner in a gas turbine engine combustor
EP1479975A1 (en) * 2003-05-20 2004-11-24 Snecma Moteurs Combustion chamber having a flexible joint between a chamber base and a chamber wall

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1265031A1 (en) * 2001-06-06 2002-12-11 Snecma Moteurs Fixing of metallic cowls on turbomachine combustion chamber liners made of CMC materials
EP1265033A1 (en) * 2001-06-06 2002-12-11 Snecma Moteurs Combustion chamber with a system for mounting the chamber end wall
EP1431665A2 (en) * 2002-12-20 2004-06-23 General Electric Company Mounting assembly for the forward end of a ceramic matrix composite liner in a gas turbine engine combustor
EP1479975A1 (en) * 2003-05-20 2004-11-24 Snecma Moteurs Combustion chamber having a flexible joint between a chamber base and a chamber wall

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3056665A1 (en) * 2014-12-05 2016-08-17 Rolls-Royce Corporation Gas turbine engine and process of coupling a first to a second component in a gas turbine engine
US10480321B2 (en) 2014-12-05 2019-11-19 Rolls-Royce Corporation Attachment of piloting feature
US11193375B2 (en) 2014-12-05 2021-12-07 Rolls-Royce Corporation Attachment of piloting feature
EP3211311B1 (en) * 2016-02-25 2020-07-22 General Electric Company Combuster assembly

Also Published As

Publication number Publication date
FR2887015B1 (en) 2010-09-24
RU2006120529A (en) 2007-12-20
US7849696B2 (en) 2010-12-14
RU2400674C2 (en) 2010-09-27
FR2887015A1 (en) 2006-12-15
JP2006349336A (en) 2006-12-28
CA2548905A1 (en) 2006-12-14
US20070107710A1 (en) 2007-05-17
EP1734305A3 (en) 2013-05-01
EP1734305B1 (en) 2014-07-02
CA2548905C (en) 2013-09-17

Similar Documents

Publication Publication Date Title
EP1734305B1 (en) Assembly of an annular combustion chamber for a turbine
EP1818615B1 (en) Annular combustion chamber of a turbomachine
EP1265031B1 (en) Fixing of metallic cowls on turbomachine combustion chamber liners made of CMC materials
EP1265035B1 (en) Double mounting of a ceramic matrix composite combustion chamber
EP1265034B1 (en) Mounting of a turbine ceramic matrix composite combustion chamber with brazed mounting lugs
EP1873385B1 (en) Exhaust cone for channeling a gas stream downstream of a turbine
EP1265036B1 (en) Elastic mounting of a ceramic matrix composite combustion chamber inside a metallic casing
EP1265032A1 (en) Ceramic matrix composite material gas turbine combustion chamber
EP1265033B1 (en) Combustion chamber with a system for mounting the chamber end wall
EP1265037A1 (en) Fixation of turbine ceramic matrix composite combustion chamber using dilution holes
EP1479975A1 (en) Combustion chamber having a flexible joint between a chamber base and a chamber wall
EP2598803A2 (en) Fuel injection system for turbojet engine and method of assembling such an injection system
EP4240955B1 (en) Fastening of an exhaust cone in a turbomachine nozzle
FR2825778A1 (en) Coupling between fuel injector nozzle and turbine combustion chamber base has metal mixer/deflector assembly sliding in composition base aperture
FR2896575A1 (en) Annular combustion chamber for e.g. turbo propeller, has chamber base arranged between inner and outer walls in region that is provided upstream to chamber, where chamber base and walls are made of ceramic material
FR2825782A1 (en) Turbine with metal casing has composition combustion chamber fitted with sliding coupling to allow for differences in expansion coefficients
EP4226034B1 (en) Sealing assembly for a turbine ejection cone
EP4486986A1 (en) Ejection cone for an aircraft turbine engine
FR3133411A1 (en) Assembly of an ejection cone in a turbomachine nozzle
FR3111964A1 (en) Assembly of a combustion chamber part by overlapping another part
FR2694600A1 (en) Silencer construction for IC engine of motor vehicle - comprises central gas-carrying conduit, surrounded by cylindrical casing and end plates, casing being slidable over sealing joint members

Legal Events

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

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20060523

AK Designated contracting states

Kind code of ref document: A2

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

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

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

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

RIC1 Information provided on ipc code assigned before grant

Ipc: F23R 3/60 20060101ALI20130326BHEP

Ipc: F23R 3/00 20060101AFI20130326BHEP

AKX Designation fees paid

Designated state(s): DE FR GB IT SE

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20140120

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB IT SE

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602006042111

Country of ref document: DE

Effective date: 20140814

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602006042111

Country of ref document: DE

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

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

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 10

26N No opposition filed

Effective date: 20150407

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 11

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 12

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES, FR

Effective date: 20170719

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 13

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

Ref country code: GB

Payment date: 20240419

Year of fee payment: 19

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

Ref country code: DE

Payment date: 20240418

Year of fee payment: 19

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

Ref country code: IT

Payment date: 20240418

Year of fee payment: 19

Ref country code: FR

Payment date: 20240418

Year of fee payment: 19

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

Ref country code: SE

Payment date: 20240418

Year of fee payment: 19