EP2040001B1 - Annular combustion chamber for a gas turbine engine - Google Patents

Annular combustion chamber for a gas turbine engine Download PDF

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Publication number
EP2040001B1
EP2040001B1 EP08164751.3A EP08164751A EP2040001B1 EP 2040001 B1 EP2040001 B1 EP 2040001B1 EP 08164751 A EP08164751 A EP 08164751A EP 2040001 B1 EP2040001 B1 EP 2040001B1
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EP
European Patent Office
Prior art keywords
wall
chamber
combustion chamber
openings
combustion
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EP08164751.3A
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German (de)
French (fr)
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EP2040001A3 (en
EP2040001A2 (en
Inventor
Didier Hippolyte Hernandez
Thomas Olivier Marie Noel
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00012—Details of sealing devices

Definitions

  • the present invention relates to the field of gas turbine engines, aims the annular combustion chambers of these engines and more particularly the combustion chamber bottoms.
  • Combustion chambers according to the relevant prior art are disclosed in the documents EP 1818615 A1 , and EP 1731839 .
  • a conventional annular combustion chamber is illustrated on the figure 1 . It is an axial half-section with respect to the axis of the engine of such a chamber the other half being deduced by symmetry with respect to this axis.
  • the combustion chamber 110 is housed in a diffusion chamber 130 which is an annular space defined between an outer casing 132 and an inner casing 134, in which compressed air is introduced from an upstream compressor not shown through An annular diffusion duct 136.
  • This conventional combustion chamber 110 has an outer wall 112 and an inner wall 114 which are coaxial and substantially conical to make the connection between the compressor duct and the turbine duct.
  • the outer 112 and inner 114 walls are interconnected upstream by a wall forming the chamber bottom 116.
  • the chamber bottom is an annular frustoconical piece which extends between two substantially transverse planes flaring from downstream to upstream.
  • the bottom chamber is connected to each of the two walls 112 and 114 by annular flanges 116 e and 116 i.
  • the chamber bottom is pierced with orifices 118 through which the injection systems 120 of fuel premixed with the combustion air pass. These orifices are angularly distributed around the motor axis. fireplaces are produced downstream of the injection systems.
  • the plane of the orifices is perpendicular to the axis of the combustion foci.
  • the axis combustion burners 200 are divergent, of angle ⁇ with respect to the axis of the motor.
  • thermal protection screens designated deflectors 122.
  • deflectors 122 are plates substantially refractory refractory material with an opening corresponding to that of the orifices of the injection systems.
  • the baffles are centered on the latter and fixed by brazing on the chamber bottom. They are cooled by cooling air jets entering the chamber through cooling bores 124 in the wall of the chamber bottom. These jets of air flowing from upstream to downstream are guided by chamber fairings 126, pass through the bottom chamber 116 and come to cool by impact the upstream face of the deflectors 122.
  • the invention therefore aims to allow the attachment of the deflectors on the wall of the chamber bottom despite the small space between two adjacent holes.
  • the invention relates to an annular combustion chamber of a gas turbine engine having an outer wall and an inner wall connected by a wall forming a chamber bottom, the walls delimiting combustion zones of axes inclined with respect to the axis. of the chamber, the chamber bottom wall, of frustoconical shape, being pierced with orifices for the fuel injection systems, the plane of the orifices being perpendicular to the axes of the combustion foci, thermal protection baffles centered on each orifices having a shoulder by which they bear against a flat surface portion along the periphery of the orifices.
  • the combustion chamber is characterized in that the chamber bottom wall is shaped in a succession of adjacent flat facets having a common edge, with a facet by injection system orifice, the shoulder of the deflectors bearing against the facet plane.
  • intersection of the planes of two adjacent facets forms a straight line passing through the axis of the combustion chamber.
  • the facets are then made by simply folding sheet.
  • This type of bottom wall construction advantageously applies when the minimum distance between two adjacent orifices is less than a value E which corresponds to the minimum sheet width in order to be able to produce flat surfaces with a transition zone according to FIG. prior art. Indeed, beyond this value, there are two solutions for producing the chamber bottom. The solution according to the prior art and the solution according to the invention. Below this value only the solution of the invention remains possible.
  • An evaluation of this value E is equal to the formula 9 * e + 2 * p + 5 in millimeters, in which "e” corresponds to the thickness of the sheet forming the bottom of the chamber and p the width of the shoulder or the bearing surface of the shoulder of the deflector.
  • the baffles comprise a flat surface portion lined with two radial sealing walls with the chamber bottom.
  • the invention also relates to a gas turbine engine comprising such a combustion chamber.
  • FIG. 2 a part of the chamber wall 116 seen from the side of the interior of the chamber without the annular walls is seen.
  • the two visible holes for the injection systems are circular and planar. They are bordered by a flat bearing surface 116a. These surfaces 116a form a flat support for the shoulders of the baffles, and are obtained by deformation by stamping the sheet forming the bottom chamber. Since the surface 116 is conical and has the same axis as the motor axis, the deformation is minimal along the generatrix G1 of the cone which passes through the diameter of the orifice and the deformation is maximum along the generatrix G2 which is tangent at the orifices, that is to say in the narrowest zone between two adjacent apertures.
  • the figure 3 shows, in section along the III - III direction, the shape of the wall in this zone.
  • the figure 4 shows the assembly of a deflector, in section along a generatrix G1.
  • This deflector 122 comprises a cylindrical flange 122a adapted to be housed in the opening of the chamber bottom.
  • the outer surface of this flange comprises a shoulder 122b which abuts on the bearing surface 116a.
  • a sleeve 123 holds the deflector against the bearing surface 116a. Everything is properly brazed.
  • the figure 5 shows the mounting of the deflector seen in the area of the figure 3 .
  • the shoulder 122b of the two deflectors 122 bears against the bearing surface 116a of the wall 116.
  • Walls 122c extending along the lateral edges and oriented radially with respect to the axis of the chamber, ensure sealing and prevent gases from the combustion chamber from circulating in the space between the bottom of the chamber and the baffle. These walls are perpendicular to the plane of the deflector
  • This zone is suitably cooled by unrepresented holes for the impact cooling air jets.
  • this minimum value below which the deformation of the sheet is mechanically no longer possible by means of industrial metal working, is substantially equal in millimeters to the value expressed by the following formula: 9 * e + 2 * p + 5 where "e” is the thickness of the sheet forming the bottom wall of the chamber and "p" the width of the shoulder 122b corresponding to the width that must be provided for the bearing surface 116a.
  • the figure 6 shows such a case of chamber bottom wall 116 'where the orifices are too close together for the sinking between the bearing surface 116'a is still possible.
  • the minimum value of the space separating two through-holes of the fuel injectors is 21.5 mm.
  • This wall geometry thus limits the possibilities of evolution of the chambers using more elaborate injection systems.
  • the annular chamber bottom wall 16 extends between two flanges, a radially inner flange 16i and a radially outer flange 16e through which the wall is fixed to the inner and outer walls of the annular combustion chamber, not shown because not concerned by the invention.
  • the wall comprises the orifices 16s for the injection systems.
  • the generally frustoconical wall consists of plane facets 16f surrounding each of the orifices 16s. These facets are thus delimited by four sides two sides in an arc 16f1 and 16f2.
  • the radially inner side 16f1 is bordered by the flange 16i for attachment to the inner wall of the combustion chamber.
  • the radially outer side 16f2 is bordered by the attachment flange 16e to the outer wall of the combustion chamber.
  • the other two sides 16f3 and 16f4 are rectilinear and are common to two adjacent facets. They are oriented in a radial direction passing through the axis of the engine. These sides are obtained by simply folding sheet.
  • the deflector 22 comprises a flat wall 22p which is positioned parallel to the flat facet of the chamber bottom.
  • a circular flange 22a borders the orifice corresponding to that of the chamber bottom.
  • This flange externally comprises a shoulder 22b which bears on the flat surface of the facet 16f.
  • Two side walls 22m seal between two adjacent baffles.
  • the deflector optionally has an excess thickness 22c.
  • this zone is shown in section on the chamber bottom between two adjacent orifices.
  • Two deflectors 22 are supported, by their shoulder 22b, on their respective facet 16f bordering the orifices of the injection systems.
  • the baffles are each held by a sheath, not shown here, slid around the circular flange on the other side with respect to the shoulder 22b and clasped together with the shoulder 22b the chamber bottom wall 16f.
  • the transition zones between flat surface portions and conical surface portions are dispensed with, and the number of fuel injectors can be increased. / or injection systems of larger diameter for better combustion.
  • the baffles being planar, the space between the bottom wall of the chamber and the baffles are flat, ensuring a flow of the cooling air homogeneous in this space.
  • the chamber is of divergent type, that is to say that the apex of the cone formed by the wall of the chamber bottom is downstream with respect to it and the axes of the combustion zones associated with the injectors deviate from the motor shaft downstream.
  • the invention also applies to a combustion chamber of convergent type, that is to say whose apex of the cone formed by the chamber bottom wall is located upstream with respect to itself and the axes of the Combustion points associated with the injectors are approaching the axis of the engine downstream.

Description

La présente invention se rapporte au domaine des moteurs à turbine à gaz, vise les chambres de combustion annulaires de ces moteurs et plus particulièrement les fonds de chambre de combustion. Des chambres de combustion selon l'art antérieur pertinent sont divulguées dans les documents EP 1818615 A1 , et EP 1731839 . Une chambre de combustion annulaire conventionnelle est illustrée sur la figure 1. Il s'agit d'une demi-coupe axiale par rapport à l'axe du moteur d'une telle chambre l'autre moitié se déduisant par symétrie par rapport à cet axe. La chambre de combustion 110 est logée dans une chambre de diffusion 130 qui est un espace annulaire défini entre un carter externe 132 et un carter interne 134, dans lequel est introduit l'air comprimé provenant d'un compresseur amont non représenté par l'intermédiaire d'un conduit annulaire de diffusion 136. Cette chambre de combustion conventionnelle 110 comporte une paroi externe 112 et une paroi interne 114 qui sont coaxiales et sensiblement coniques pour faire la liaison entre la veine de compresseur et la veine de turbine. Les parois externe 112 et interne 114 sont reliées entre elles à l'amont par une paroi formant le fond de chambre 116.The present invention relates to the field of gas turbine engines, aims the annular combustion chambers of these engines and more particularly the combustion chamber bottoms. Combustion chambers according to the relevant prior art are disclosed in the documents EP 1818615 A1 , and EP 1731839 . A conventional annular combustion chamber is illustrated on the figure 1 . It is an axial half-section with respect to the axis of the engine of such a chamber the other half being deduced by symmetry with respect to this axis. The combustion chamber 110 is housed in a diffusion chamber 130 which is an annular space defined between an outer casing 132 and an inner casing 134, in which compressed air is introduced from an upstream compressor not shown through An annular diffusion duct 136. This conventional combustion chamber 110 has an outer wall 112 and an inner wall 114 which are coaxial and substantially conical to make the connection between the compressor duct and the turbine duct. The outer 112 and inner 114 walls are interconnected upstream by a wall forming the chamber bottom 116.

Le fond de chambre est une pièce tronconique annulaire qui s'étend entre deux plans sensiblement transversaux en s'évasant de l'aval vers l'amont. Le fond de chambre se raccorde à chacune des deux parois 112 et 114 par des brides annulaires 116 e et 116i.The chamber bottom is an annular frustoconical piece which extends between two substantially transverse planes flaring from downstream to upstream. The bottom chamber is connected to each of the two walls 112 and 114 by annular flanges 116 e and 116 i.

Le fond de chambre est percé d'orifices 118 à travers lesquels passent les systèmes d'injection 120 de carburant prémélangé à l'air de combustion. Ces orifices sont répartis angulairement autour de l'axe moteur. Des foyers de combustion sont produits en aval des systèmes d'injection. Le plan des orifices est perpendiculaire à l'axe des foyers de combustion. Dans l'exemple représenté, les foyers de combustion d'axe 200 sont divergents, d'angle α par rapport à l'axe du moteur.The chamber bottom is pierced with orifices 118 through which the injection systems 120 of fuel premixed with the combustion air pass. These orifices are angularly distributed around the motor axis. Fireplaces are produced downstream of the injection systems. The plane of the orifices is perpendicular to the axis of the combustion foci. In the example shown, the axis combustion burners 200 are divergent, of angle α with respect to the axis of the motor.

Pour protéger le fond de chambre du rayonnement de chaleur, il est prévu des écrans de protection thermique désignés déflecteurs 122. Ces déflecteurs sont des plaques en matériau réfractaire sensiblement planes avec une ouverture correspondant à celle des orifices des systèmes d'injection. Les déflecteurs sont centrés sur ces derniers et fixés par brasage sur le fond de chambre. Ils sont refroidis par des jets d'air de refroidissement pénétrant dans la chambre à travers des perçages de refroidissement 124 dans la paroi du fond de chambre. Ces jets d'air s'écoulant d'amont vers l'aval sont guidés par des carénages de chambre 126, traversent le fond de chambre 116 et viennent refroidir par impact la face amont des déflecteurs 122.To protect the bottom of the chamber from heat radiation, there are provided thermal protection screens designated deflectors 122. These deflectors are plates substantially refractory refractory material with an opening corresponding to that of the orifices of the injection systems. The baffles are centered on the latter and fixed by brazing on the chamber bottom. They are cooled by cooling air jets entering the chamber through cooling bores 124 in the wall of the chamber bottom. These jets of air flowing from upstream to downstream are guided by chamber fairings 126, pass through the bottom chamber 116 and come to cool by impact the upstream face of the deflectors 122.

En raison de la conicité de la paroi du fond de chambre, on ménage des surfaces d'appui plan autour des orifices des systèmes d'injection sur lesquelles on applique les épaulements des déflecteurs. La paroi de fond de chambre étant une tôle, ces surfaces d'appui sont réalisées par emboutissage local. Un soyage assure le raccord entre la surface emboutie et la surface conique de la tôle.Because of the conicity of the wall of the chamber bottom, plane bearing surfaces are provided around the orifices of the injection systems to which the shoulders of the deflectors are applied. The bottom wall of the chamber being a sheet, these bearing surfaces are made by local stamping. A trimming ensures the connection between the stamped surface and the conical surface of the sheet.

L'évolution technologique conduit à la réalisation de systèmes d'injection de plus grand diamètre. Par ailleurs on cherche à disposer de foyers de combustion répartis autour de l'axe de la chambre aussi rapprochés que possible les uns des autres de façon à obtenir une combustion optimale.Technological evolution leads to the realization of injection systems of larger diameter. Furthermore, it is sought to have combustion foci distributed around the axis of the chamber as close as possible to one another so as to obtain optimal combustion.

Il se pose alors le problème de réaliser des surfaces d'appui par emboutissage dans la zone la plus étroite entre deux orifices adjacents. Le rapprochement des orifices ne permet pas la réalisation de ces surfaces d'appui par emboutissage.There then arises the problem of making bearing surfaces by stamping in the narrowest zone between two adjacent orifices. The approximation of the orifices does not allow the realization of these bearing surfaces by stamping.

L'invention a donc pour objectif de permettre la fixation des déflecteurs sur la paroi du fond de chambre malgré le faible espace séparant deux orifices adjacents.The invention therefore aims to allow the attachment of the deflectors on the wall of the chamber bottom despite the small space between two adjacent holes.

Ainsi l'invention porte sur une chambre de combustion annulaire de moteur à turbine à gaz comportant une paroi externe et une paroi interne reliées par une paroi formant fond de chambre les parois délimitant des foyers de combustion d'axes inclinés par rapport à l'axe de la chambre, la paroi de fond de chambre, de forme tronconique, étant percée d'orifices pour les systèmes d'injection de carburant, les plans des orifices étant perpendiculaires aux axes des foyers de combustion, des déflecteurs de protection thermique centrés sur chacun des orifices comportant un épaulement par lequel ils sont en appui contre une portion de surface plane le long du pourtour des orifices.Thus, the invention relates to an annular combustion chamber of a gas turbine engine having an outer wall and an inner wall connected by a wall forming a chamber bottom, the walls delimiting combustion zones of axes inclined with respect to the axis. of the chamber, the chamber bottom wall, of frustoconical shape, being pierced with orifices for the fuel injection systems, the plane of the orifices being perpendicular to the axes of the combustion foci, thermal protection baffles centered on each orifices having a shoulder by which they bear against a flat surface portion along the periphery of the orifices.

Conformément à l'invention la chambre de combustion est caractérisé par le fait que la paroi de fond de chambre est conformée en une succession de facettes planes adjacentes présentant un bord commun, avec une facette par orifice de système d'injection, l'épaulement des déflecteurs étant en appui contre le plan des facettes.According to the invention the combustion chamber is characterized in that the chamber bottom wall is shaped in a succession of adjacent flat facets having a common edge, with a facet by injection system orifice, the shoulder of the deflectors bearing against the facet plane.

La surface de la paroi de fond de chambre correspondant à un déflecteur étant plane, il n'est plus nécessaire de ménager des zones d'appui par emboutissage. La réalisation en est largement simplifiée. Les formes de paroi assurant la transition entre les zones planes et les zones présentant une conicité ne sont plus nécessaires. On peut enfin réaliser des déflecteurs à surface plane ce qui est avantageux en fabrication.Since the surface of the chamber bottom wall corresponding to a deflector is flat, it is no longer necessary to provide support zones by stamping. The realization is greatly simplified. Wall shapes that transition from flat to tapered areas are no longer needed. Finally flat surface deflectors can be made, which is advantageous in manufacturing.

De préférence l'intersection des plans de deux facettes adjacentes forme une droite passant par l'axe de la chambre de combustion. Les facettes sont alors réalisées par simple pliage de tôle.Preferably the intersection of the planes of two adjacent facets forms a straight line passing through the axis of the combustion chamber. The facets are then made by simply folding sheet.

Ce type de réalisation de paroi de fond de chambre s'applique avantageusement lorsque la distance minimale entre deux orifices adjacents est inférieure à une valeur E qui correspond à la largeur de tôle minimale pour pouvoir réaliser des surfaces planes avec une zone de transition selon l'art antérieur. En effet au-delà de cette valeur on dispose des deux solutions de réalisation du fond de chambre. La solution selon l'art antérieur et la solution selon l'invention. En deçà de cette valeur seule la solution de l'invention reste possible. Une évaluation de cette valeur E est égale à la formule 9*e + 2* p + 5 en millimètres, dans laquelle « e » correspond à l'épaisseur de la tôle formant le fond de chambre et p la largeur de l'épaulement ou de la surface d'appui de l'épaulement du déflecteur.This type of bottom wall construction advantageously applies when the minimum distance between two adjacent orifices is less than a value E which corresponds to the minimum sheet width in order to be able to produce flat surfaces with a transition zone according to FIG. prior art. Indeed, beyond this value, there are two solutions for producing the chamber bottom. The solution according to the prior art and the solution according to the invention. Below this value only the solution of the invention remains possible. An evaluation of this value E is equal to the formula 9 * e + 2 * p + 5 in millimeters, in which "e" corresponds to the thickness of the sheet forming the bottom of the chamber and p the width of the shoulder or the bearing surface of the shoulder of the deflector.

Selon un mode de réalisation les déflecteurs comprennent une portion de surface plane bordée de deux murets d'étanchéité radiale avec le fond de chambre.According to one embodiment the baffles comprise a flat surface portion lined with two radial sealing walls with the chamber bottom.

L'invention porte aussi sur un moteur à turbine à gaz comportant une telle chambre de combustion.The invention also relates to a gas turbine engine comprising such a combustion chamber.

D'autres caractéristiques et avantages ressortiront de la description qui suit d'un mode de réalisation non limitatif de l'invention en référence aux dessins annexés sur lesquels

  • La figure 1 représente en demi coupe axiale une chambre de combustion annulaire de moteur à turbine à gaz conventionnelle ;
  • La figure 2 montre une vue partielle en perspective d'une paroi de fond de chambre seule conformée selon la technique de l'art antérieur ;
  • La figure 3 est une coupe selon la direction III-III de la figure 2
  • La figure 4 montre le mode de fixation courant d'un déflecteur sur une paroi de fond de chambre ;
  • La figure 5 montre en coupe la disposition des déflecteurs au niveau de la zone la plus étroite entre deux orifices adjacents ;
  • La figure 6 montre en perspective une paroi de fond de chambre selon l'enseignement de l'art antérieur lorsque les orifices sont trop rapprochés ;
  • La figure 7 montre en perspective la solution de l'invention où la paroi du fond de chambre est conformée en facettes planes centrées sur les orifices des systèmes d'injection ;
  • La figure 8 montre un déflecteur convenant à la paroi de fond de chambre de l'invention vu en perspective ;
  • La figure 9 montre en coupe la solution de l'invention dans l'espace entre deux orifices de systèmes d'injection adjacents.
Other features and advantages will become apparent from the following description of a non-limiting embodiment of the invention with reference to the accompanying drawings in which:
  • The figure 1 represents in half an axial section an annular combustion chamber of a conventional gas turbine engine;
  • The figure 2 shows a partial perspective view of a single chamber bottom wall shaped according to the technique of the prior art;
  • The figure 3 is a section along the III-III direction of the figure 2
  • The figure 4 shows the current fixation mode of a deflector on a chamber bottom wall;
  • The figure 5 shows in section the disposition of the deflectors at the level of the narrowest zone between two adjacent orifices;
  • The figure 6 shows in perspective a chamber bottom wall according to the teaching of the prior art when the orifices are too close together;
  • The figure 7 shows in perspective the solution of the invention wherein the wall of the chamber bottom is shaped in planar facets centered on the orifices of the injection systems;
  • The figure 8 shows a deflector suitable for the chamber bottom wall of the invention seen in perspective;
  • The figure 9 shows in section the solution of the invention in the space between two ports of adjacent injection systems.

En se reportant à la figure 2, on voit une partie de la paroi 116 de fond de chambre vue du côté de l'intérieur de la chambre sans les parois annulaires. Les deux orifices visibles pour les systèmes d'injection sont circulaires et plans. Ils sont bordés d'une surface d'appui plane 116a. Ces surfaces 116a forment un appui plan pour les épaulements des déflecteurs, et sont obtenues par déformation par emboutissage de la tôle constituant le fond de chambre. La surface 116 étant conique et de même axe que l'axe moteur, la déformation est minimale le long de la génératrice G1 du cône qui passe par le diamètre de l'orifice et la déformation est maximale le long de la génératrice G2 qui est tangente aux orifices c'est-à-dire dans la zone la plus étroite entre deux orifice adjacents.Referring to the figure 2 a part of the chamber wall 116 seen from the side of the interior of the chamber without the annular walls is seen. The two visible holes for the injection systems are circular and planar. They are bordered by a flat bearing surface 116a. These surfaces 116a form a flat support for the shoulders of the baffles, and are obtained by deformation by stamping the sheet forming the bottom chamber. Since the surface 116 is conical and has the same axis as the motor axis, the deformation is minimal along the generatrix G1 of the cone which passes through the diameter of the orifice and the deformation is maximum along the generatrix G2 which is tangent at the orifices, that is to say in the narrowest zone between two adjacent apertures.

La figure 3 montre, en coupe selon la direction III - III, la forme de la paroi dans cette zone. Sur la distance E entre les deux orifices on a deux portions planes 116a formant surfaces d'appui de largeur p, deux zones de transition arrondies de largeur t et la paroi conique du fond de chambre sur une largeur c.The figure 3 shows, in section along the III - III direction, the shape of the wall in this zone. On the distance E between the two orifices there are two flat portions 116a forming bearing surfaces of width p, two rounded transition zones of width t and the conical wall of the chamber bottom over a width c.

La figure 4 montre le montage d'un déflecteur, en coupe le long d'une génératrice G1. Ce déflecteur 122 comprend une bride cylindrique 122a adaptée pour être logée dans l'orifice du fond de chambre. La surface extérieure de cette bride comprend un épaulement 122b qui vient s'appuyer sur la surface d'appui 116a. Un fourreau 123 maintient le déflecteur contre la surface d'appui 116a. Le tout est convenablement brasé.The figure 4 shows the assembly of a deflector, in section along a generatrix G1. This deflector 122 comprises a cylindrical flange 122a adapted to be housed in the opening of the chamber bottom. The outer surface of this flange comprises a shoulder 122b which abuts on the bearing surface 116a. A sleeve 123 holds the deflector against the bearing surface 116a. Everything is properly brazed.

La figure 5 montre le montage du déflecteur vu dans la zone de la figure 3. L'épaulement 122b des deux déflecteurs 122 est en appui sur la surface d'appui 116a de la paroi 116. Des murets 122c, s'étendant le long des bords latéraux et orientés radialement par rapport à l'axe de la chambre, assurent l'étanchéité et évitent que des gaz de la chambre de combustion ne viennent circuler dans l'espace entre le fond de la chambre et le déflecteur. Ces murets sont perpendiculaires au plan du déflecteurThe figure 5 shows the mounting of the deflector seen in the area of the figure 3 . The shoulder 122b of the two deflectors 122 bears against the bearing surface 116a of the wall 116. Walls 122c, extending along the lateral edges and oriented radially with respect to the axis of the chamber, ensure sealing and prevent gases from the combustion chamber from circulating in the space between the bottom of the chamber and the baffle. These walls are perpendicular to the plane of the deflector

Cette zone est convenablement refroidie par des perçages non représentés pour les jets d'air de refroidissement par impact.This zone is suitably cooled by unrepresented holes for the impact cooling air jets.

Lorsque les orifices des systèmes d'injection augmentent en diamètre ou bien lorsque leur nombre devient important la distance E séparant deux orifices adjacents devient insuffisante pour permettre la réalisation par emboutissage à la fois des surfaces d'appui 116a et des zones de transition.When the orifices of the injection systems increase in diameter or when their number becomes large, the distance E separating two adjacent orifices becomes insufficient to enable the stamping of both bearing surfaces 116a and transition zones.

On détermine que cette valeur minimale, en deçà de laquelle la déformation de la tôle n'est mécaniquement plus possible par des moyens de travail des métaux industriels, est sensiblement égale en millimètres à la valeur exprimée par la formule suivante : 9*e + 2*p + 5 où « e » est l'épaisseur de la tôle formant la paroi de fond de chambre et « p » la largeur de l'épaulement 122b correspondant à la largeur qu'il faut prévoir pour la surface d'appui 116a. La figure 6 montre un tel cas de paroi de fond de chambre 116' où les orifices sont trop rapprochés pour que le soyage entre les surface d'appui 116'a soit encore possible.It is determined that this minimum value, below which the deformation of the sheet is mechanically no longer possible by means of industrial metal working, is substantially equal in millimeters to the value expressed by the following formula: 9 * e + 2 * p + 5 where "e" is the thickness of the sheet forming the bottom wall of the chamber and "p" the width of the shoulder 122b corresponding to the width that must be provided for the bearing surface 116a. The figure 6 shows such a case of chamber bottom wall 116 'where the orifices are too close together for the sinking between the bearing surface 116'a is still possible.

Par exemple pour une valeur e = 1,5 mm et p= 1,5 mm, la valeur minimale de l'espace séparant deux orifices de passage des injecteurs de carburant, est de 21,5 mm.For example, for a value e = 1.5 mm and p = 1.5 mm, the minimum value of the space separating two through-holes of the fuel injectors is 21.5 mm.

Cette géométrie de paroi limite donc les possibilités d'évolution des chambres mettant en oeuvre des systèmes d'injection plus élaborés.This wall geometry thus limits the possibilities of evolution of the chambers using more elaborate injection systems.

On a représenté sur la figure 7 la solution de l'invention. La paroi de fond de chambre 16 annulaire s'étend entre deux brides, une bride radialement interne 16i et une bride radialement externe 16e par lesquels la paroi est fixée aux parois interne et externe de la chambre de combustion annulaire, non représentée car non concernée par l'invention.We have shown on the figure 7 the solution of the invention. The annular chamber bottom wall 16 extends between two flanges, a radially inner flange 16i and a radially outer flange 16e through which the wall is fixed to the inner and outer walls of the annular combustion chamber, not shown because not concerned by the invention.

La paroi comprend les orifices 16s pour les systèmes d'injection. La paroi de forme générale tronconique est constituée de facette planes 16f entourant chacun des orifices 16s. Ces facettes sont donc délimitées par quatre côtés deux côtés en arc de cercle 16f1 et 16f2. Le côté 16f1 radialement intérieur est bordé par la bride 16i de fixation à la paroi interne de la chambre de combustion. Le côté 16f2 radialement extérieur est bordé par la bride 16e de fixation à la paroi externe de la chambre de combustion. Les deux autres côtés 16f3 et 16f4 sont rectilignes et sont communs à deux facettes adjacentes. Ils sont orientés selon une direction radiale passant par l'axe du moteur. Ces côtés sont obtenus par simple pliage de tôle.The wall comprises the orifices 16s for the injection systems. The generally frustoconical wall consists of plane facets 16f surrounding each of the orifices 16s. These facets are thus delimited by four sides two sides in an arc 16f1 and 16f2. The radially inner side 16f1 is bordered by the flange 16i for attachment to the inner wall of the combustion chamber. The radially outer side 16f2 is bordered by the attachment flange 16e to the outer wall of the combustion chamber. The other two sides 16f3 and 16f4 are rectilinear and are common to two adjacent facets. They are oriented in a radial direction passing through the axis of the engine. These sides are obtained by simply folding sheet.

Non seulement la paroi est plus simple à réaliser en raison de la simplification de sa géométrie mais aussi l'efficacité est accrue.Not only the wall is simpler to achieve because of the simplification of its geometry but also the efficiency is increased.

On a représenté sur la figure 8 un déflecteur convenant à cette nouvelle géométrie de fond de chambre. Le déflecteur 22 comprend une paroi plane 22p qui vient se positionner parallèlement à la facette plane du fond de chambre. Une bride circulaire 22a borde l'orifice correspondant à celui du fond de chambre. Cette bride comprend extérieurement un épaulement 22b qui vient prendre appui sur la surface plane de la facette 16f. Deux murets latéraux 22m assurent l'étanchéité entre deux déflecteurs adjacents. Dans la zone correspondant à l'espace entre deux déflecteurs adjacents le déflecteur présente le cas échéant une surépaisseur 22c.We have shown on the figure 8 a deflector suitable for this new chamber bottom geometry. The deflector 22 comprises a flat wall 22p which is positioned parallel to the flat facet of the chamber bottom. A circular flange 22a borders the orifice corresponding to that of the chamber bottom. This flange externally comprises a shoulder 22b which bears on the flat surface of the facet 16f. Two side walls 22m seal between two adjacent baffles. In the zone corresponding to the space between two adjacent deflectors, the deflector optionally has an excess thickness 22c.

Sur la figure 9, on a représenté en coupe cette zone sur le fond de chambre entre deux orifices adjacents. Deux déflecteurs 22 sont en appui, par leur épaulement 22b, sur leur facette 16f respective bordant les orifices des systèmes d'injection. Les déflecteurs sont maintenus chacun par un fourreau, ici non représenté, glissé autour de la bride circulaire de l'autre côté par rapport à l'épaulement 22b et enserrant ensemble avec l'épaulement 22b la paroi de fond de chambre 16f.On the figure 9 this zone is shown in section on the chamber bottom between two adjacent orifices. Two deflectors 22 are supported, by their shoulder 22b, on their respective facet 16f bordering the orifices of the injection systems. The baffles are each held by a sheath, not shown here, slid around the circular flange on the other side with respect to the shoulder 22b and clasped together with the shoulder 22b the chamber bottom wall 16f.

Ainsi par la forme en facette de la paroi de fond de chambre, on s'affranchit de la réalisation de zones de transition entre des portions de surface planes et des portions de surfaces coniques, on peut avoir des injecteurs de carburant en plus grand nombre et/ou des systèmes d'injection de plus grand diamètre pour une meilleure combustion. En outre les déflecteurs étant plans, l'espace entre la paroi de fond de chambre et les déflecteurs sont plans assurant un écoulement de l'air de refroidissement homogène dans cet espace.Thus, by the facet shape of the chamber bottom wall, the transition zones between flat surface portions and conical surface portions are dispensed with, and the number of fuel injectors can be increased. / or injection systems of larger diameter for better combustion. In addition, the baffles being planar, the space between the bottom wall of the chamber and the baffles are flat, ensuring a flow of the cooling air homogeneous in this space.

Selon l'exemple de réalisation représenté la chambre est de type divergente, c'est-à-dire que le sommet du cône formé par la paroi du fond de chambre est en aval par rapport à elle et les axes des foyers de combustion associés aux injecteurs s'écartent de l'axe moteur vers l'aval.According to the exemplary embodiment shown, the chamber is of divergent type, that is to say that the apex of the cone formed by the wall of the chamber bottom is downstream with respect to it and the axes of the combustion zones associated with the injectors deviate from the motor shaft downstream.

L'invention s'applique également à une chambre de combustion de type convergente, c'est-à-dire dont le sommet du cône formé par la paroi de fond de chambre est situé en amont par rapport à elle-même et les axes des foyers de combustion associés aux injecteurs se rapprochent de l'axe du moteur vers l'aval.The invention also applies to a combustion chamber of convergent type, that is to say whose apex of the cone formed by the chamber bottom wall is located upstream with respect to itself and the axes of the Combustion points associated with the injectors are approaching the axis of the engine downstream.

Claims (8)

  1. Annular combustion chamber (110) of a gas turbine engine, comprising an external wall (112) and an internal wall (114) which are connected by a wall (16) forming the bottom of the chamber, said walls delimiting combustion furnaces whose axes are tilted with respect to the axis of the chamber, the wall (16) of the bottom of the chamber, in the shape of a truncated cone, being drilled to form openings (16s) for fuel injection systems, the planes of the openings being perpendicular to the axes of said combustion furnaces, thermal protection deflectors (22) centred on each of the openings (16s) comprising a flat shoulder (22b) by means of which they are supported against a flat surface portion along the periphery of the openings (16s), the wall (16) of the bottom of the chamber being formed as a succession of flat adjacent facets (16f) having a common border, with one facet per opening (16s), the shoulder (22b) of the deflectors (22) being supported against the plane of the facets (16f), characterised by the fact that the minimum distance between two adjacent openings (16s) is smaller than a value of E = 9*e + 2*p + 5 in mm, "e" corresponding to the thickness of the sheet metal forming the wall (16) of the bottom of the chamber and "p" corresponding to the width of said shoulder (22b).
  2. Chamber according to the preceding claim, wherein the intersection of the planes of two adjacent facets forms a straight line (16f 3, 16f4) passing through the axis of the combustion chamber.
  3. Combustion chamber according to one of the preceding claims, wherein the minimum distance between two openings (16s) is smaller than 21.5mm for a wall thickness of e = 1.5mm.
  4. Combustion chamber according to the preceding claim, wherein the width of the shoulder (22b) is p = 1.5mm.
  5. Combustion chamber according to one of the preceding claims, wherein the deflectors (22) comprise a flat surface portion (22p) bordered by two radial sealing walls (22m) with the bottom of the chamber.
  6. Convergent-type combustion chamber according to one of the preceding claims.
  7. Divergent-type combustion chamber according to one of claims 1 to 5.
  8. Gas turbine engine comprising a combustion chamber according to one of the preceding claims.
EP08164751.3A 2007-09-21 2008-09-19 Annular combustion chamber for a gas turbine engine Active EP2040001B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0706644A FR2921462B1 (en) 2007-09-21 2007-09-21 ANNULAR COMBUSTION CHAMBER FOR A GAS TURBINE ENGINE

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EP2040001A2 EP2040001A2 (en) 2009-03-25
EP2040001A3 EP2040001A3 (en) 2010-02-17
EP2040001B1 true EP2040001B1 (en) 2018-04-18

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US (1) US8156744B2 (en)
EP (1) EP2040001B1 (en)
CA (1) CA2639588C (en)
FR (1) FR2921462B1 (en)
RU (1) RU2485405C2 (en)

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Publication number Publication date
RU2008137660A (en) 2010-03-27
CA2639588A1 (en) 2009-03-21
CA2639588C (en) 2016-03-29
FR2921462B1 (en) 2012-08-24
RU2485405C2 (en) 2013-06-20
FR2921462A1 (en) 2009-03-27
US20090077976A1 (en) 2009-03-26
EP2040001A3 (en) 2010-02-17
EP2040001A2 (en) 2009-03-25
US8156744B2 (en) 2012-04-17

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