EP0565441A1 - Combustion chamber with premixing generator - Google Patents
Combustion chamber with premixing generator Download PDFInfo
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- EP0565441A1 EP0565441A1 EP93400906A EP93400906A EP0565441A1 EP 0565441 A1 EP0565441 A1 EP 0565441A1 EP 93400906 A EP93400906 A EP 93400906A EP 93400906 A EP93400906 A EP 93400906A EP 0565441 A1 EP0565441 A1 EP 0565441A1
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- European Patent Office
- Prior art keywords
- combustion chamber
- section
- fuel
- branches
- upstream
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Classifications
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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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
- F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
- F23D2900/11001—Impinging-jet injectors or jet impinging on a surface
Definitions
- combustion chambers for turbo-machines comprising: an axis of sensitive symmetry; inner and outer annular walls with respect to said axis; a bottom, which extends transversely with respect to said axis and which, in cooperation with said internal and external walls, delimits a combustion chamber; fuel injectors, which pass through said bottom; and, a source of oxidizer under pressure.
- the present invention provides such a system by providing a particular constitution of the bottom of the combustion chamber.
- the bottom comprises at least two first profiles each having a V-shaped cross section, the tip of the V being oriented upstream relative to the combustion chamber, each of said first profiles being disposed substantially symmetrically with respect to a radial plane passing through the axis of symmetry and containing the edge of this first profile passing through the point of the V of its cross section, however a first passage is made between the ends of the adjacent branches of two successive first profiles and that at least one fuel injector is contained within a space delimited by the edges and by the ends of said adjacent branches of said two successive first profiles and has fuel injection orifices provided injection axes which intersect said adjacent branches.
- the main advantage of the invention lies in obtaining a pre-vaporization, therefore an effective premix in an axially limited space.
- each first profile 5 is constituted by a substantially rectangular plate, folded along its largest median so as to have a cross section ( Figure 3) V-shaped, and an edge 14 , which constitutes the apex of the angle of the dihedral thus formed, on the one hand contained in a radial plane 15 passing through the axis 2, on the other hand extending substantially perpendicular to the axis 2, being further oriented so that the point of the V is opposite to the combustion chamber 7.
- each first profile 5 is arranged substantially symmetrically with respect to said radial plane 15, the edges 16 of the two adjacent branches of two first successive sections 5 being spaced from one another and delimiting a first passage 17 for communication of the combustion chamber 7 with the space 10.
- the injection nozzles 12 and 13 are arranged opposite the external faces es 5Ades first sections 5, so that their fuel injection axes 12A, 13A intersect said faces 5A.
- Each second profile 6 is constituted by a substantially rectangular plate, folded along its largest median so as to have a cross-section in shape (Figure 3) of V, and an edge 18, which constitutes the apex of the angle of the dihedral thus formed, on the one hand contained in a radial plane 19 passing through the axis 2, on the other hand extending substantially perpendicularly to the axis 2, being further oriented so that the tip of the V is directed towards the combustion chamber 7.
- the branches of the V of each second profile 6 are arranged substantially symmetrically with respect to said radial plane 19.
- Each second section 6 is substantially contained in the space delimited by the edges 14 and 16 of the two adjacent branches of two successive first sections 5, so that the external faces 6A of the branches of the second profiles 6 are arranged, each, facing the external face 5A of a branch of a first profile 5, and, that a second passage 20 is defined between said external faces 6A and 5A, connects the space 10 to the combustion chamber 7 and either the edges 14 of the dihedrons of the first profiles 5 converge towards the end edges 16 of the branches of the first profiles 5, that is to say also towards the combustion chamber 7.
- orifices through 21 are formed in the second sections 6, to allow the passage of the fuel injection nozzles 12, 13, with a clearance between each fuel injection nozzle and the edge delimiting the orifice 21, in order to provide a passage of oxidant between said fuel injection nozzle and selvedge.
- the orifices 21 are substantially coaxial with the axes 12A, 13A of fuel injection.
- the embodiment of Figure 4 is close to the previous one. It differs therefrom, on the one hand, by the fixing, by welding (22), of the second sections 6 directly on the fuel conduits 11, and not on the internal 1 and external 3 walls, on the other hand, by the constitution of the first profiles by double walls 105-205 leaving between them a space 123 for circulating oxidizer, finally, by the elimination of the fuel injection nozzles 12, 13 and their replacement by fuel injection holes 112 , 113 formed in the fuel line 11, whose injection axes 112A, 113A intersect the external faces 105A of the upstream walls 105 of the first sections.
- the other provisions are retained and are therefore not described again.
- a first passage 117 is formed between the end edges 116 of the branches of the first profiles 105-205, and a second passage 120 is formed between the faces 6A and 105A and converges towards the combustion chamber 7.
- the internal space 123 of each first section 102-205 communicates with the passage 120, on the one hand, through orifices 124 formed in the wall 105 near the edge 114 of the dihedral 105-205, upstream of the intersection zones of the axes 112A, 113A and faces 105A, on the other hand, by orifices 125 formed in the wall 105 near the edges 116 of the ends of the branches of the first profiles 105-205, downstream of said points of intersection.
- the first sections 105-205 like those, 5, of the first embodiment described, are fixed (welded) to the internal 1 and external 3 walls.
- the fuel from the fuel injection nozzles 12, 13 is projected onto the faces 5A. These, delimiting the combustion chamber 7, are hot, which causes vaporization of the fuel. Furthermore, the oxidant coming from space 10, on the one hand, passes through passages 20 and 17, and performs its mixing, without combustion, with the vaporized fuel. A fuel / oxidizer premix is produced in an axially limited space. Hence the possibility to produce compact combustion chambers, and therefore light, although also effective with regard to the reduction of emissions of nitrogen oxides, in particular at the full gas regime.
- the oxidizer which penetrates inside the Vs of the second sections 6 and exits through the orifices 21 contributes to improving the entrainment of the fuel vaporized in the main oxidant stream which flows in each second passage 20 towards the 'combustion chamber 7.
- the convergence of said second passages 20 enhances the efficiency of the fuel and premix drive.
- FIG. 4 benefits from the advantages which have just been mentioned.
- the fixing of the second sections 6 directly on the fuel lines 11 makes it possible both to improve the axial compactness, and to reduce the weight of the fixing.
- the oxidizer which penetrates into the spaces 123 of the first profiles 105-205 through the orifices 124 and exits therefrom through the orifices 125 performs cooling of said first profiles 105-205, favorable to improving their service life, and , there too, coming out through the orifices 125, complete the effect of driving the fuel produced by the main flow of oxidizer which passes through the second passages 120 and flows towards the combustion chamber 7.
- the presence of the second sections makes it possible to produce passages 20; 120 converging, more oriented, and perfecting both the efficiency of the mixture and that of its drive towards the combustion chamber 7, in particular obtaining an acceleration of the mixture when crossing the first passages 17; 117, suitable for eliminating the risks of self-ignition.
- the reduced size of the pencil injectors makes it easy and preferred to adopt, but not exclusive, the adoption of fuel injectors of other types.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
Description
On connait des chambres de combustion pour turbo-machines comprenant : un axe de sensible symétrie ; des parois interne et externe annulaires par rapport audit axe ; un fond, qui s'étend transversalement par rapport audit axe et qui, en coopération avec lesdites parois interne et externe, délimite une enceinte de combustion ; des injecteurs de carburant, qui traversent ledit fond ; et, une source de comburant sous pression.There are known combustion chambers for turbo-machines comprising: an axis of sensitive symmetry; inner and outer annular walls with respect to said axis; a bottom, which extends transversely with respect to said axis and which, in cooperation with said internal and external walls, delimits a combustion chamber; fuel injectors, which pass through said bottom; and, a source of oxidizer under pressure.
L'une des préoccupations actuelles majeures des concepteurs de turbo-machines est la réduction des émissions d'oxydes d'azote. On sait que les systèmes d'injection de carburant utilisant le principe du prémélange du carburant avec le comburant, avant la combustion proprement dite, permettent la réduction souhaitée des émissions d'oxydes d'azote.One of the major concerns of turbo-machine designers today is the reduction of nitrogen oxide emissions. It is known that fuel injection systems using the principle of premixing the fuel with the oxidant, before combustion proper, allow the desired reduction of nitrogen oxide emissions.
La présente invention propose un tel système en prévoyant une constitution particulière du fond de la chambre de combustion.The present invention provides such a system by providing a particular constitution of the bottom of the combustion chamber.
Acet effet, selon l'invention, le fond comprend au moins deux premiers profilés ayant chacun une section droite en forme de V, la pointe du V étant orientée vers l'amont par rapport à l'enceinte de combustion, chacun desdits premiers profilés étant disposé sensiblement symétriquement par rapport à un plan radial passant par l'axe de symétrie et contenant l'arête de ce premier profilé passant par la pointe du V de sa section droite, cependant qu'un premier passage est ménagé entre les extrémités des branches adjacentes de deux premiers profilés successifs et qu'au moins un injecteur de carburant est contenu à l'intérieur d'un espace délimité par les arêtes et par les extrémités desdites branches adjacentes des deuxdits premiers profilés successifs et possède des orifices d'injection de carburant munis d'axes d'injections qui intersectent lesdites branches adjacentes.Acet effect, according to the invention, the bottom comprises at least two first profiles each having a V-shaped cross section, the tip of the V being oriented upstream relative to the combustion chamber, each of said first profiles being disposed substantially symmetrically with respect to a radial plane passing through the axis of symmetry and containing the edge of this first profile passing through the point of the V of its cross section, however a first passage is made between the ends of the adjacent branches of two successive first profiles and that at least one fuel injector is contained within a space delimited by the edges and by the ends of said adjacent branches of said two successive first profiles and has fuel injection orifices provided injection axes which intersect said adjacent branches.
Les avantageuses dispositions suivantes sont en outre de préférence adoptées :
- - ledit injecteur de carburant est contenu à l'intérieur d'un deuxième profilé ayant une section droite en forme de V, la pointe du V étant orientée vers l'aval, ce deuxième profilé ayant deux branches disposées en regard desdites branches adjacentes des deux premiers profilés successifs, respectivement, un deuxième passage étant ménagé entre chaque branche du deuxième profilé et la branche d'un premier profilé disposé en regard, cependant que des orifices sont ménagés dans les branches du deuxième profilé et sont sensiblement coaxiaux des orifices d'injection de carburant dudit injecteur de carburant ;
- - chaque deuxième passage est convergent de l'amont vers l'aval ;
- - chaque deuxième profilé est indépendant de l'injecteur de carburant qu'il contient ;
- - chaque deuxième profilé est soudé sur l'injecteur de carburant qu'il contient ;
- - chaque premier profilé comprend une paroi aval, et, une paroi amont qui y est assemblée, en ménageant entre ces parois aval et amont un troisième espace qui communique, par des orifices amont et par des orifices aval traversant la paroi amont, avec l'environnement extérieur dudit premier profilé ;
- - lesdits injecteurs de carburant sont du type injecteur-crayon.
- - Said fuel injector is contained inside a second section having a V-shaped cross section, the tip of the V being oriented downstream, this second section having two branches arranged opposite said adjacent branches of the two first successive sections, respectively, a second passage being formed between each branch of the second section and the branch of a first section arranged opposite, while orifices are provided in the branches of the second section and are substantially coaxial with the injection orifices fuel from said fuel injector;
- - each second pass converges from upstream to downstream;
- - Each second profile is independent of the fuel injector it contains;
- - each second profile is welded to the fuel injector it contains;
- - Each first section comprises a downstream wall, and an upstream wall which is assembled therein, providing between these downstream and upstream walls a third space which communicates, by upstream orifices and by downstream orifices passing through the upstream wall, with the external environment of said first profile;
- - Said fuel injectors are of the injector-pencil type.
L'avantage principal de l'invention réside dans l'obtention d'une prévaporisation, donc d'un prémélange efficace dans un espace axialement limité.The main advantage of the invention lies in obtaining a pre-vaporization, therefore an effective premix in an axially limited space.
L'invention sera mieux comprise, et des caractéristiques secondaires et leurs avantages apparaîtront au cours de la description de réalisations donnée ci-dessous à titre d'exemple.The invention will be better understood, and secondary characteristics and their advantages will appear during the description of embodiments given below by way of example.
Il est entendu que la description et les dessins ne sont donnés qu'à titre indicatif et non limitatif.It is understood that the description and the drawings are given for information only and are not limiting.
Il sera fait référence aux dessins annexés, dans lesquels :
- - la figure 1 est une coupe axiale schématisée d'une chambre de combustion conforme à l'invention :
- - la figure 2 est une coupe suivant II-II de la figure 1 ;
- - la figure 3 est une coupe suivant III-III de la figure 2 ; et,
- - la figure 4 est une coupe analogue à celle de la figure 3 d'une variante de réalisation d'une chambre de combustion, également conforme à l'invention.
- FIG. 1 is a diagrammatic axial section of a combustion chamber according to the invention:
- - Figure 2 is a section along II-II of Figure 1;
- - Figure 3 is a section along III-III of Figure 2; and,
- - Figure 4 is a section similar to that of Figure 3 of an alternative embodiment of a combustion chamber, also according to the invention.
La figure 1 représente une chambre de combustion conforme à l'invention, destinée à une turbo-machine. Cette chambre de combustion comporte :
- - une paroi interne 1, annulaire, d'axe de
symétrie 2 ; - - une paroi externe 3, également annulaire, d'axe 2 ;
- - un fond 4, comportant notamment des
premiers profilés 5 et desdeuxièmes profilés 6, dont les formes et les emplacements sont définis ci-après, mais qui, d'une manière générale, s'étendent transversalement par rapport à l'axe 2, et délimitent, en coopération avec les parois interne 1 et externe 3, l'enceinte decombustion 7 ; - - une enveloppe interne 8, annulaire, d'axe 2 et une enveloppe externe 9, annulaire, d'axe 2, qui délimitent ensemble un
espace 10, à l'intérieur duquel est contenu ladite enceinte decombustion 7 et les parois la délimitant, ledit espace communiquant avec une source de comburant sous pression, schématisée par la flèche F et de préférence constituée par une turbo-soufflante ; - - des conduits de
carburant 11, qui s'étendent radialement et comportant chacun deux paires de 12, 13 d'injection de carburant, lesbuses buses 12, les plus proches de la paroi externe 3, étant destinées à l'alimentation en carburant au régime du ralenti, et, les buses,13, les plus proches de la paroi interne 1, étant destinées à l'alimentation en carburant au régime de pleins gaz. Il est à noter que, de préférence, comme dans les réalisatons représentées, les parties desconduits 11 contenues entre les parois interne 1 et externe 3 et situées en amont du fond 4, à l'extérieur de l'enceinte de combustion proprement dite 7, complétées par lesbuses 12 et 13, constituent des injecteurs de carburant dits "injecteurs-crayons". Lesconduits 11 sont montés sur l'enveloppe externe 9.
- - An
inner wall 1, annular, of axis ofsymmetry 2; - - an
outer wall 3, also annular, ofaxis 2; - a bottom 4, comprising in particular
first sections 5 andsecond sections 6, the shapes and locations of which are defined below, but which, in general, extend transversely to theaxis 2, and delimit, in cooperation with theinternal walls 1 and external 3, thecombustion chamber 7; - an
inner casing 8, annular, ofaxis 2 and anouter casing 9, annular, ofaxis 2, which together delimit aspace 10, inside which is contained saidcombustion chamber 7 and the walls delimiting it, said space communicating with a source of oxidizer under pressure, shown diagrammatically by arrow F and preferably consisting of a turbo-fan; - -
fuel lines 11, which extend radially and each comprising two pairs of 12, 13, thefuel injection nozzles nozzles 12, closest to theouter wall 3, being intended for fuel supply at idle speed, and, nozzles, 13, closest to theinternal wall 1, being intended for fuel supply at idle speed full throttle regime. It should be noted that, preferably, as in the embodiments shown, the parts of theconduits 11 contained between the internal 1 and external 3 walls and located upstream from the bottom 4, outside of theactual combustion chamber 7 , supplemented by 12 and 13, constitute fuel injectors called "pencil injectors". Thenozzles conduits 11 are mounted on theouter casing 9.
Dans la réalisation des figures 1 à 3, chaque premier profilé 5 est constitué par une plaque sensiblement rectangulaire, pliée le long de sa plus grande médiane de manière à posséder une section droite transversale (figure 3) en forme de V, et une arête 14, qui constitue le sommet de l'angle du dièdre ainsi constitué, d'une part contenue dans un plan radial 15 passant par l'axe 2, d'autre part s'étendant sensiblement perpendiculairement à l'axe 2, en étant en outre orientée de manière que la pointe du V soit opposée à l'enceinte de combustion 7. De plus, les branches du V de chaque premier profilé 5 sont disposées sensiblement symétriquement par rapport audit plan radial 15, les arêtes 16 des deux branches adjacentes de deux premiers profilés 5 successifs étant écartées l'une de l'autre et délimitant un premier passage 17 de communication de l'enceinte de combustion 7 avec l'espace 10. Les buses d'injection 12 et 13 sont disposées en regard des faces externes 5Ades premiers profilés 5, de manière que leurs axes d'injection de carburant 12A, 13A intersectent lesdites faces 5A.In the embodiment of Figures 1 to 3, each
Par ailleurs, les conduits de carburant 11 sont contenus dans des deuxièmes profilés 6. Chaque deuxième profilé 6 est constitué par une plaque sensiblement rectangulaire, pliée le long de sa plus grande médiane de manière à posséder une section droite transversale (figure 3) en forme de V, et une arête 18, qui constitue le sommet de l'angle du dièdre ainsi constitué, d'une part contenue dans un plan radial 19 passant par l'axe 2, d'autre part s'étendant sensiblement perpendiculairement à l'axe 2, en étant en outre orientée de manière que la pointe du V soit dirigée vers l'enceinte de combustion 7. De plus, les branches du V de chaque deuxième profilé 6 sont disposées sensiblement symétriquement par rapport audit plan radial 19. Chaque deuxième profilé 6 est sensiblement contenu dans l'espace délimité par les arêtes 14 et 16 des deux branches adjacentes de deux premiers profilés 5 successifs, de manière que les faces externes 6A des branches des deuxièmes profilés 6 soient disposées, chacune, en regard de la face externe 5A d'une branche d'un premier profilé 5, et, qu'un deuxième passage 20 soit défini entre lesdites faces externes 6A et 5A, relie l'espace 10 à la chambre de combustion 7 et soit convergent des arêtes 14 des dièdres des premiers profilés 5 vers les arêtes d'extrémité 16 des branches des premiers profilés 5, c'est-à-dire aussi vers l'enceinte de combustion 7. Enfin, des orifices traversant 21 sont ménagés dans les deuxièmes profilés 6, afin de permettre le passage des buses d'injection de carburant 12, 13, avec un jeu entre chaque buse d'injection de carburant et la lisière délimitant l'orifice 21, afin de ménager un passage de comburant entre lesdites buse d'injection de carburant et lisière. Les orifices 21 sont sensiblement coaxiaux avec les axes 12A, 13A d'injection de carburant.Furthermore, the
La réalisation de la figure 4 est proche de la précédente. Elle s'en distingue, d'une part, par la fixation, par soudure (22), des deuxièmes profilés 6 directement sur les conduits de carburant 11, et non sur les parois interne 1 et externe 3, d'autre part, par la constitution des premiers profilés par des parois doubles 105-205 ménageant entre elles un espace 123 de circulation de comburant, enfin, par la suppression des buses d'injection de carburant 12, 13 et leur remplacement par des trous d'injection de carburant 112, 113 ménagés dans le conduit de carburant 11, dont les axes d'injection 112A, 113A intersectent les faces externes 105A des parois amont 105 des premiers profilés. Les autres dispositions sont conservées et ne sont donc pas de nouveau décrites. Un premier passage 117 est ménagé entre les arêtes d'extrémité 116 des branches des premiers profilés 105-205, et, un deuxième passage 120 est ménagé entre les faces 6A et 105Aet converge vers l'enceinte de combustion 7. L'espace 123 interne de chaque premier profilé 102-205 communique avec le passage 120, d'une part, par des orifices traversant 124 ménagés dans la paroi 105 à proximité de l'arête 114 du dièdre 105-205, en amont des zones d'intersection des axes 112A, 113A et des faces 105A, d'autre part, par des orifices 125 ménagés dans la paroi 105 à proximité des arêtes 116 d'extrémité des branches des premiers profilés 105-205, en aval desdits points d'intersection. Dans cette deuxième réalisation, les premiers profilés 105-205, comme ceux, 5, de la première réalisation décrite, sont fixés (soudés) sur les parois interne 1 et externe 3.The embodiment of Figure 4 is close to the previous one. It differs therefrom, on the one hand, by the fixing, by welding (22), of the
Le fonctionnement de telles chambres de combustion est exposé ci-après.The operation of such combustion chambers is explained below.
Selon la réalisation des figures 1 à 3, le carburant provenant des buses d'injection de carburant 12, 13 est projeté sur les faces 5A. Celles-ci, délimitant l'enceinte de combustion 7, sont chaudes, ce qui provoque une vaporisation du carburant. Par ailleurs, le comburant provenant de l'espace 10, d'une part, traverse les passages 20 et 17, et réalise son mélange, sans combustion, avec le carburant vaporisé. Il y a réalisation d'un prémélange carburant/comburant, dans un espace axialement limité. D'où la possibilité de réaliser des chambres de combustion compactes, et par conséquent légères, bien qu'également efficaces en ce qui concerne la réduction des émissions d'oxydes d'azotes, notamment au régime de pleins gaz. Bien entendu, le comburant qui pénètre à l'intérieur des V des deuxièmes profilés 6 et en ressort par les orifices 21 contribue à améliorer l'entrainement du carburant vaporisé dans le courant principal de comburant qui s'écoule dans chaque deuxième passage 20 vers l'enceinte de combustion 7. La convergence desdits deuxièmes passages 20 renforce l'efficacité de l'entrainement du carburant et du prémélange.According to the embodiment of Figures 1 to 3, the fuel from the
La réalisation de la figure 4 bénéficie des avantages qui viennent d'être mentionnés. De plus, la fixation des deuxièmes profilés 6 directement sur les conduits de carburant 11 permet à la fois d'améliorer la compacité axiale, et, de réduire le poids de la fixation. Par ailleurs, le comburant qui pénètre dans les espaces 123 des premiers profilés 105-205 par les orifices 124 et en ressort par les orifices 125 réalise une réfrigération desdits premiers profilés 105-205, favorable à l'amélioration de leur durée de vie, et, là aussi en ressortant par les orifices 125, complètent l'effet d'entraînement du carburant réalisé par le flux principal de comburant qui traverse les deuxièmes passages 120 et s'écoule vers l'enceinte de combustion 7.The embodiment of FIG. 4 benefits from the advantages which have just been mentioned. In addition, the fixing of the
Il y a lieu de noter que la seule présence des premiers profilés 5 ; 105-205 suffit à réaliser la vaporisation du carburant avant l'enceinte de combustion 7 et son mélange avec le comburant avant réalisation de la combustion.It should be noted that the mere presence of the
Bien entendu, la présence des deuxièmes profilés permet de réaliser des passages 20 ; 120 convergents, de plus orientés, et de parfaire à la fois l'efficacité du mélange et celle de son entraînement vers l'enceinte de combustion 7, avec notamment l'obtention d'une accélération du mélange à la traversée des premiers passages 17 ; 117, propice à éliminer les risques d'auto-inflammation.Of course, the presence of the second sections makes it possible to produce
L'encombrement réduit des injecteurs-crayons en rend l'adoption aisée et préférée, mais non exclusive de l'adoption d'injecteurs de carburant d'autres types.The reduced size of the pencil injectors makes it easy and preferred to adopt, but not exclusive, the adoption of fuel injectors of other types.
L'invention n'est pas limitée aux réalisations décrites, mais en couvre au contraire toutes les variantes qui pourraient leur être apportées sans sortir de leur cadre, ni de leur esprit.The invention is not limited to the embodiments described, but on the contrary covers all the variants which could be made to them without departing from their scope or their spirit.
Claims (7)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9204281A FR2689964B1 (en) | 1992-04-08 | 1992-04-08 | COMBUSTION CHAMBER PROVIDED WITH A PREMIXED GENERATOR BOTTOM. |
FR9204281 | 1992-04-08 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0565441A1 true EP0565441A1 (en) | 1993-10-13 |
EP0565441B1 EP0565441B1 (en) | 1996-06-26 |
Family
ID=9428620
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP93400906A Expired - Lifetime EP0565441B1 (en) | 1992-04-08 | 1993-04-07 | Combustion chamber with premixing generator |
Country Status (4)
Country | Link |
---|---|
US (1) | US5341645A (en) |
EP (1) | EP0565441B1 (en) |
DE (1) | DE69303314T2 (en) |
FR (1) | FR2689964B1 (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2909437A1 (en) * | 2006-12-04 | 2008-06-06 | Snecma Sa | Rectilinear radial flame-holder device i.e. flame-holder arm for turbojet engine, has shell/cover and fuel injecting tube extended in gutter, where device is arranged such that fuel is injected in gas stream through wall of gutter |
CN102519054A (en) * | 2012-01-06 | 2012-06-27 | 北京大学 | On-duty flame stabilizer |
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GB1184379A (en) * | 1967-08-10 | 1970-03-18 | Mini Of Technology London | Improvements in or relat ing to Combustion Devices |
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- 1993-04-07 EP EP93400906A patent/EP0565441B1/en not_active Expired - Lifetime
- 1993-04-07 DE DE69303314T patent/DE69303314T2/en not_active Expired - Fee Related
- 1993-04-08 US US08/044,388 patent/US5341645A/en not_active Expired - Fee Related
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GB709452A (en) * | 1951-10-16 | 1954-05-26 | Napier & Son Ltd | Improvements in or relating to liquid fuel combustion apparatus more particularly for gas turbine plant |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2909437A1 (en) * | 2006-12-04 | 2008-06-06 | Snecma Sa | Rectilinear radial flame-holder device i.e. flame-holder arm for turbojet engine, has shell/cover and fuel injecting tube extended in gutter, where device is arranged such that fuel is injected in gas stream through wall of gutter |
CN102519054A (en) * | 2012-01-06 | 2012-06-27 | 北京大学 | On-duty flame stabilizer |
Also Published As
Publication number | Publication date |
---|---|
FR2689964B1 (en) | 1994-05-27 |
DE69303314D1 (en) | 1996-08-01 |
US5341645A (en) | 1994-08-30 |
DE69303314T2 (en) | 1996-11-28 |
FR2689964A1 (en) | 1993-10-15 |
EP0565441B1 (en) | 1996-06-26 |
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