EP0565442A1 - Combustion chamber wall - Google Patents

Combustion chamber wall Download PDF

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Publication number
EP0565442A1
EP0565442A1 EP93400907A EP93400907A EP0565442A1 EP 0565442 A1 EP0565442 A1 EP 0565442A1 EP 93400907 A EP93400907 A EP 93400907A EP 93400907 A EP93400907 A EP 93400907A EP 0565442 A1 EP0565442 A1 EP 0565442A1
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EP
European Patent Office
Prior art keywords
combustion chamber
assembly
sheets
cells
face
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EP93400907A
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German (de)
French (fr)
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EP0565442B1 (en
Inventor
Gérard Yves Georges Barbier
Xavier Marie Henri Bardey
Michel André Albert Desaulty
Eric Lancelot
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Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/181—Blades having a closed internal cavity containing a cooling medium, e.g. sodium
    • 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

Definitions

  • the invention intends, within the aforementioned framework, to propose a new arrangement allowing the structure to withstand, for short transient periods, a very high radiative thermal flux, of the order of one megawatt / m2.
  • the invention therefore relates to a combustion chamber, in particular for a turbo-machine, comprising at least a first assembly including a first fuel injection device and a first combustion zone, and, adapted to the operation of the combustion chamber. at a first speed, such as the idling speed, and also comprising at least a second assembly including a second fuel injection device and a premix zone delimited by axial walls, this second assembly being preferably provided downstream of the premix zone of a flame stabilization device and being adapted to the operation of the combustion chamber at a second speed, such as at full gas speed, said premix zone being designed for operation at a determined temperature, but being however liable to be exposed for brief periods to a maximum temperature higher than said temperature determined erasure.
  • said axial walls comprise, arranged in their thickness, cells, of which at least the face limiting the premix zone is made of a first material resistant to said maximum temperature, and which (the cells) are filled with a second material, whose melting temperature is between said determined and maximum temperatures, and whose latent heat of fusion is greater than 400 kiloJoule / kilogram mass.
  • the main advantage lies in the exceptional resistance of the walls to brief, but very intense, thermal stresses to which they are subjected.
  • the combustion chamber shown in FIG. 1 has an axis of sensitive symmetry 1; a first annular internal wall 2, of axis 1, to which is connected a first particular wall, annular 3, also of axis 1, contributing to delimit a premix chamber 4; a second annular inner wall 5, of axis 1, to which is connected a second particular wall, annular 6, of axis 1, which completes the delimitation of the premix chamber 4; an outer wall 7, annular, of axis 1; a bottom 8, which connects the outer wall 7 to the second inner wall 5; a flame stabilization device 9, placed at the outlet of the premix chamber 4, of a known type such as, for example, one of those described and shown in FR-A-2 221 621; a fuel supply ramp 10, to which are connected a fuel injector 11, adapted to operation at idle speed, and, a fuel injector 12, adapted to full speed engine; an inner envelope 13, annular, of axis 1, and, an outer envelope 14, annular, of axis 1, which delimit between them
  • the combustion chamber 16 is delimited by the first internal wall 2, the second internal wall 5, the external wall 7, and the bottom 8.
  • orifices 17 for admission of primary oxidant and orifices 18 for oxidant dilution formed in the second internal wall 5 and in the external wall 7, connect the space 15 to the combustion chamber 16.
  • the normal operation of the combustion chamber corresponds to the production, during operation in full gas mode, of a fuel-oxidizer mixture inside the premix chamber 4, without combustion in this premix chamber. 4, upon injection and ignition, in the area of the flame stabilization device 9, in the combustion chamber 16 of said mixture, as well as on injection and ignition, in said chamber of combustion 16, of the fuel projected by the fuel injectors 11.
  • each of these walls was produced as defined below with reference to FIGS. 2 and 3.
  • each wall 3, 6, is constituted by the assembly of a first sheet 20, in one of the faces of which, depressions 21, delimited by contact edges 22 , have been provided with a second sheet 23, in one of the faces of which depressions 24, delimited by contact edges 25, have been provided.
  • the shapes of the contact selvedges 22, 25 correspond, so that said selvedges can be brought into contact with one another, and that the two sheets 20, 23 are definitively assembled, for example by brazing the selvedges contact 22, 25.
  • the sheets 20 and 23 are made of a first material resistant of course to the maximum temperatures to which said sheets can be exposed. It is generally a high temperature resistant super alloy, as commonly used by turbo machine manufacturers.
  • cells 26 are provided and are filled with a second material defined below, introduced into the cells 26 when the sheets 20 and 23 are assembled.
  • the temperatures to which the particular walls 3 and 6 are exposed are between a determined temperature, corresponding to the normal operation of the combustion chamber, without combustion inside the premix chamber 4, and, a maximum temperature, higher than said determined temperature and corresponding to the exceptional operation during which combustion is carried out inside said premix chamber 4.
  • the normal, determined temperature can be of the order of 700 ° C, the maximum temperature rising to 900 ° C for a few seconds.
  • the second material is chosen so as to: a) be in the solid state at said determined temperature; b) being in the liquid state at said maximum temperature, therefore having a melting temperature between the determined and maximum temperatures; c) to have a high latent heat of fusion, greater than 400 kiloJoule / kilogram, this precisely to absorb, during its fusion, the enormous quantity of heat released by the accidental combustion carried out in the premix chamber 4, by hypothesis, without temperature rise during said fusion.
  • sodium chloride is preferably chosen.
  • the thickness of the cells 26 can be between 1 and 1.5 mm.
  • the thicknesses of the sheets 20 and 23 have similar values.
  • FIG. 3 An alternative embodiment is shown in Figure 3, in which one of the sheets of Figure 20 has been replaced by a sheet 120 having no depression.
  • the contact edges of the other sheet 23 are then in contact with the inner face 122 of the sheet 120.
  • the cells here delimited between the face 120 and the depressions 24 of the sheet 23, by the selvedges 25, are filled with the same second material as above.
  • the sheets 120 and 23 are also made of the same first material, generally consisting of a super alloy resistant to high temperatures.
  • the faces of the walls 3, 6, which delimit the premix chamber 4 are made of said first material resistant to high temperatures
  • the opposite face a priori less exposed to accidental high temperatures could be made by a less resistant material.
  • the two sheets are made of the same first material.

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

Abstract

The invention relates to a combustion chamber comprising a pre-mixing chamber. According to the invention, the walls of this pre-mixing chamber comprise cells (26), the face of which delimiting the pre-mixing zone is made of a first material which is resistant to a maximum operating temperature, and which cells are filled with a second material, the melting temperature of which is comprised between normal and maximum operating temperatures, and the latent melting heat is greater than 400 kilojoule/kilogramme mass. One application is the production of a combustion chamber comprising injectors for the idling and full-gas operating states. <IMAGE>

Description

Il est connu d'équiper les chambres de combustion, destinées notamment aux turbo-machines, de deux groupes distincts d'injecteurs de carburant. Les injecteurs de carburant du premier groupe sont adaptés au fonctionnement au régime du ralenti, alors qu'au contraire les injecteurs de carburant du deuxième groupe sont adaptés au fonctionnement au régime de plein gaz. Souvent, ces injecteurs de carburant du deuxième groupe sont situés au fond d'une chambre de prémélange.It is known to equip the combustion chambers, intended in particular for turbo-machines, with two distinct groups of fuel injectors. The fuel injectors of the first group are adapted to operation at idle speed, while on the contrary the fuel injectors of the second group are adapted to operation at full throttle speed. Often, these second group fuel injectors are located at the bottom of a premix chamber.

Il a été constaté que, de manière transitoire, une combustion non souhaitée pouvait apparaître dans cette chambre de prémélange, les parois de celle-ci étant par suite exposées à des températures très élevées soumettant la structure à des contraintes thermiques excessives, susceptibles d'endommager définitivement cette structure.It has been found that, in a transient manner, an undesired combustion could appear in this premix chamber, the walls of the latter being consequently exposed to very high temperatures subjecting the structure to excessive thermal stresses, liable to damage definitely this structure.

L'invention entend, dans le cadre précité, proposer une disposition nouvelle permettant à la structure de supporter, pendant des périodes transitoires brèves, un flux radiatif thermique très élevé, de l'ordre de un mégawatt/m2.The invention intends, within the aforementioned framework, to propose a new arrangement allowing the structure to withstand, for short transient periods, a very high radiative thermal flux, of the order of one megawatt / m2.

L'invention est donc relative à une chambre de combustion, notamment pour turbo-machine, comprenant au moins un premier ensemble incluant un premier dispositif d'injection de carburant et une première zone de combustion, et, adapté au fonctionnement de la chambre de combustion à un premier régime, tel que le régime de ralenti, et comprenant également au moins un deuxième ensemble incluant un deuxième dispositif d'injection de carburant et une zone de prémélange délimitée par des parois axiales, ce deuxième ensemble étant muni de préférence en aval de la zone de prémélange d'un dispositif de stabilisation de flamme et étant adapté au fonctionnement de la chambre de combustion à un deuxième régime, tel que le régime à plein gaz, ladite zone de prémélange étant conçue pour un fonctionnement à une température déterminée, mais étant cependant susceptible d'être exposée pendant de brèves périodes à une température maximale supérieure à ladite température déterminée.The invention therefore relates to a combustion chamber, in particular for a turbo-machine, comprising at least a first assembly including a first fuel injection device and a first combustion zone, and, adapted to the operation of the combustion chamber. at a first speed, such as the idling speed, and also comprising at least a second assembly including a second fuel injection device and a premix zone delimited by axial walls, this second assembly being preferably provided downstream of the premix zone of a flame stabilization device and being adapted to the operation of the combustion chamber at a second speed, such as at full gas speed, said premix zone being designed for operation at a determined temperature, but being however liable to be exposed for brief periods to a maximum temperature higher than said temperature determined erasure.

Selon l'invention, lesdites parois axiales comportent, ménagées dans leur épaisseur, des alvéoles, dont au moins la face limitant la zone de prémélange est constituée en un premier matériau résistant à ladite température maximale, et qui (les alvéoles) sont emplies d'un deuxième matériau, dont la température de fusion est comprise entre lesdites températures déterminée et maximale, et dont la chaleur latente de fusion est supérieure à 400 kiloJoule/kilogramme masse.According to the invention, said axial walls comprise, arranged in their thickness, cells, of which at least the face limiting the premix zone is made of a first material resistant to said maximum temperature, and which (the cells) are filled with a second material, whose melting temperature is between said determined and maximum temperatures, and whose latent heat of fusion is greater than 400 kiloJoule / kilogram mass.

Les avantageuses dispositions suivantes sont, en outre, de préférence adoptées :

  • - les parois axiales sont constituées par l'assemblage de deux feuilles, comportant chacune une face d'assemblage, la face d'assemblage d'au moins l'une des deux feuilles comportant des dépressions délimitées par des lisières de contact, qui sont en appui étanche sur la face d'assemblage de l'autre feuille, lesdites alvéoles étant délimitées par les parties desdites faces d'assemblage qui comprennent les dépressions ;
  • - les deux feuilles sont maintenues assemblées par brasage desdites lisières de contact ;
  • - chacune des deuxdites feuilles comporte des dépressions, qui sont regroupées par paire d'une dépression d'une feuille et d'une dépression de l'autre feuille pour former une alvéole ;
  • - le deuxième matériau est constitué par du chlorure de sodium.
In addition, the following advantageous arrangements are preferably adopted:
  • the axial walls are formed by the assembly of two sheets, each comprising an assembly face, the assembly face of at least one of the two sheets comprising depressions delimited by contact selvages, which are in sealing support on the assembly face of the other sheet, said cells being delimited by the parts of said assembly faces which include the depressions;
  • - The two sheets are kept assembled by brazing said contact edges;
  • - Each of said two sheets has depressions, which are grouped in pairs of a depression of a sheet and a depression of the other sheet to form a cell;
  • - The second material consists of sodium chloride.

L'avantage principal réside dans la résistance exceptionnelle des parois aux contraintes thermiques brèves, mais de très forte intensité auxquelles elles sont soumises.The main advantage lies in the exceptional resistance of the walls to brief, but very intense, thermal stresses to which they are subjected.

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 d'une chambre de combustion conforme à l'invention ;
  • - la figure 2 est un agrandissement du détail Ade la figure 1 ; et
  • - la figure 3 est une vue, analogue à celle de la figure 2, d'une variante de réalisation également conforme à l'invention.
Reference will be made to the accompanying drawings, in which:
  • - Figure 1 is an axial section of a combustion chamber according to the invention;
  • - Figure 2 is an enlargement of the detail Ade in Figure 1; and
  • - Figure 3 is a view, similar to that of Figure 2, of an alternative embodiment also according to the invention.

La chambre de combustion représentée sur la figure 1 comporte un axe de sensible symétrie 1 ; une première paroi interne annulaire 2, d'axe 1, à laquelle est raccordée une première paroi particulière, annulaire 3, également d'axe 1, contribuant à délimiter une chambre de prémélange 4 ; une deuxième paroi interne annulaire 5, d'axe 1, à laquelle est raccordée une deuxième paroi particulière, annulaire 6, d'axe 1, qui complète la délimitation de la chambre de prémélange 4 ; une paroi externe 7, annulaire, d'axe 1 ; un fond 8, qui relie la paroi externe 7 à la deuxième paroi interne 5 ; un dispositif de stabilisation de flamme 9, placé à la sortie de la chambre de prémélange 4, d'un type connu tel que, par exemple, l'un de ceux décrits et représentés dans FR-A-2 221 621 ; une rampe 10 d'alimentation en carburant, à laquelle sont raccordés un injecteur de carburant 11, adapté au fonctionnement au régime de ralenti, et, un injecteur de carburant 12, adapté au régime de plein gaz ; une enveloppe interne 13, annulaire, d'axe 1, et, une enveloppe externe 14, annulaire, d'axe 1, qui délimitent entre elles un espace 15, à l'intérieur duquel sont contenues les diverses parois annulaires déjà énumérées 2, 3, 5, 6, 7, et qui communique en amont avec une source de comburant sous pression, schématisée par la flèche F, et constituée généralement par un compresseur hélicoïdal. L'enceinte de combustion 16 est délimitée par la première paroi interne 2, la deuxième paroi interne 5, la paroi externe 7, et le fond 8. De manière connue, des orifices 17 d'admission de comburant primaire et des orifices 18 de comburant de dilution, ménagés dans la deuxième paroi interne 5 et dans la paroi externe 7, relient l'espace 15 à l'enceinte de combustion 16.The combustion chamber shown in FIG. 1 has an axis of sensitive symmetry 1; a first annular internal wall 2, of axis 1, to which is connected a first particular wall, annular 3, also of axis 1, contributing to delimit a premix chamber 4; a second annular inner wall 5, of axis 1, to which is connected a second particular wall, annular 6, of axis 1, which completes the delimitation of the premix chamber 4; an outer wall 7, annular, of axis 1; a bottom 8, which connects the outer wall 7 to the second inner wall 5; a flame stabilization device 9, placed at the outlet of the premix chamber 4, of a known type such as, for example, one of those described and shown in FR-A-2 221 621; a fuel supply ramp 10, to which are connected a fuel injector 11, adapted to operation at idle speed, and, a fuel injector 12, adapted to full speed engine; an inner envelope 13, annular, of axis 1, and, an outer envelope 14, annular, of axis 1, which delimit between them a space 15, inside which are contained the various annular walls already listed 2, 3 , 5, 6, 7, and which communicates upstream with a source of oxidizer under pressure, shown diagrammatically by the arrow che F, and generally constituted by a helical compressor. The combustion chamber 16 is delimited by the first internal wall 2, the second internal wall 5, the external wall 7, and the bottom 8. In known manner, orifices 17 for admission of primary oxidant and orifices 18 for oxidant dilution, formed in the second internal wall 5 and in the external wall 7, connect the space 15 to the combustion chamber 16.

Les injecteurs de carburant 11, adaptés au fonctionnement au régime de ralenti, traversent le fond 8 et débouchent à l'intérieur de l'enceinte de combustion 16. Les injecteurs de carburant 12 adaptés au fonctionnement au régime de plein gaz, débouchent dans la chambre de prémélange 4, celle-ci étant en communication directe avec l'espace 15, par l'intermédiaire de son embouchure amont 19, située à l'extrémité de cette chambre de prémélange qui est opposée à celle, aval, où est situé le dispositif de stabilisation de flamme 9.The fuel injectors 11, suitable for operation at idle speed, pass through the bottom 8 and open into the combustion chamber 16. The fuel injectors 12 suitable for operation at full gas speed, open into the chamber of premix 4, this being in direct communication with space 15, via its upstream mouth 19, located at the end of this premix chamber which is opposite to that, downstream, where the device is located flame stabilization 9.

En principe, le fonctionnement normal de la chambre de combustion correspond à la réalisation, lors du fonctionnement en régime de plein gaz, d'un mélange carburant-comburant à l'intérieur de la chambre de prémélange 4, sans combustion dans cette chambre de prémélange 4, à l'injection et à l'inflammation, dans la zone du dispositif de stabilisation de flamme 9, dans l'enceinte de combustion 16 dudit mélange, ainsi qu'à l'injection et à l'inflammation, dans ladite enceinte de combustion 16, du carburant projeté par les injecteurs de carburant 11. Il a cependant été constaté que parfois une combustion non désirée apparaissait à l'intérieur de la chambre de prémélange 4. Pour permettre aux première paroi particulière 3 et deuxième paroi particulière 6 de supporter ce flux radiatif thermique exceptionnellement grand, mais bref, chacune de ces parois a été réalisée comme défini ci-après en regard des figures 2 et 3.In principle, the normal operation of the combustion chamber corresponds to the production, during operation in full gas mode, of a fuel-oxidizer mixture inside the premix chamber 4, without combustion in this premix chamber. 4, upon injection and ignition, in the area of the flame stabilization device 9, in the combustion chamber 16 of said mixture, as well as on injection and ignition, in said chamber of combustion 16, of the fuel projected by the fuel injectors 11. However, it has been found that sometimes an unwanted combustion appears inside the premix chamber 4. To allow the first particular wall 3 and second particular wall 6 to support this exceptionally large, but brief, radiative thermal flux, each of these walls was produced as defined below with reference to FIGS. 2 and 3.

Selon le premier mode de réalisation de la figure 2, chaque paroi 3, 6, est constituée par l'assemblage d'une première feuille 20, dans l'une des faces de laquelle, des dépressions 21, délimitées par des lisières de contact 22, ont été ménagées, avec une deuxième feuille 23, dans l'une des faces de laquelle des dépressions 24, délimitées par des lisières de contact 25, ont été ménagées. Les formes des lisières de contact 22, 25 se correspondent, de manière que lesdites lisières puissent être mises en contact les unes sur les autres, et que les deux feuilles 20, 23 soient définitivement assemblées, par exemple au moyen d'un brasage des lisières de contact 22, 25.According to the first embodiment of Figure 2, each wall 3, 6, is constituted by the assembly of a first sheet 20, in one of the faces of which, depressions 21, delimited by contact edges 22 , have been provided with a second sheet 23, in one of the faces of which depressions 24, delimited by contact edges 25, have been provided. The shapes of the contact selvedges 22, 25 correspond, so that said selvedges can be brought into contact with one another, and that the two sheets 20, 23 are definitively assembled, for example by brazing the selvedges contact 22, 25.

Les feuilles 20 et 23 sont réalisées en un premier matériau résistant bien entendu aux températures maximales auxquelles lesdites feuilles peuvent être exposées. Il s'agit généralement d'un super alliage résistant aux températures élevées, tel qu'utilisé couramment par les fabricants de turbo-machines.The sheets 20 and 23 are made of a first material resistant of course to the maximum temperatures to which said sheets can be exposed. It is generally a high temperature resistant super alloy, as commonly used by turbo machine manufacturers.

Entre les lisières de contact, des alvéoles 26 sont ménagées et sont emplies d'un deuxième matériau défini ci-après, introduit dans les alvéoles 26 au moment de l'assemblage des feuilles 20 et 23.Between the contact edges, cells 26 are provided and are filled with a second material defined below, introduced into the cells 26 when the sheets 20 and 23 are assembled.

Avant de préciser les caractéristiques dudit deuxième matériau, il convient d'observer que les températures auxquelles sont exposées les parois particulières 3 et 6 sont comprises entre une température déterminée, correspondant au fonctionnement normal de la chambre de combustion, sans combustion à l'intérieur de la chambre de prémélange 4, et, une température maximale, supérieure à ladite température déterminée et correspondant au fonctionnement exceptionnel pendant lequel une combustion est réalisée à l'intérieur de ladite chambre de prémélange 4. A titre indicatif, la température normale, déterminée peut être de l'ordre de 700°C, la température maximale s'élevant à 900°C pendant quelques secondes.Before specifying the characteristics of said second material, it should be observed that the temperatures to which the particular walls 3 and 6 are exposed are between a determined temperature, corresponding to the normal operation of the combustion chamber, without combustion inside the premix chamber 4, and, a maximum temperature, higher than said determined temperature and corresponding to the exceptional operation during which combustion is carried out inside said premix chamber 4. As an indication, the normal, determined temperature can be of the order of 700 ° C, the maximum temperature rising to 900 ° C for a few seconds.

Dans ces conditions, le deuxième matériau est choisi, de manière : a) à être à l'état solide à ladite température déterminée ; b) à être à l'état liquide à ladite température maximale, donc avoir une température de fusion comprise entre les températures déterminée et maximale ; c) à avoir une chaleur latente de fusion élevée, supérieure à 400 kiloJoule/kilogramme, ceci précisément pourabsorber, lors de sa fusion, l'énorme quantité de chaleur dégagée par la combustion accidentelle réalisée dans la chambre de prémélange 4, par hypothèse, sans élévation de température lors de ladite fusion. Parmi les matériaux convenant à cette application, le chlorure de sodium est de préférence choisi. Sa chaleur latente de fusion est égale à 500 kiloJoule/kilogramme, de sorte qu'il suffit de prévoir une petite quantité de ce deuxième matériau pour éviter tout dommage aux parois 3 et 6 résultant d'une éventuelle élévation anormale de leurs températures. Ainsi, l'épaisseur des alvéoles 26 peut être comprise entre 1 et 1,5 mm. Les épaisseurs des feuilles 20 et 23 ont des valeurs analogues.Under these conditions, the second material is chosen so as to: a) be in the solid state at said determined temperature; b) being in the liquid state at said maximum temperature, therefore having a melting temperature between the determined and maximum temperatures; c) to have a high latent heat of fusion, greater than 400 kiloJoule / kilogram, this precisely to absorb, during its fusion, the enormous quantity of heat released by the accidental combustion carried out in the premix chamber 4, by hypothesis, without temperature rise during said fusion. Among the materials suitable for this application, sodium chloride is preferably chosen. Its latent heat of fusion is equal to 500 kiloJoule / kilogram, so that it suffices to provide a small amount of this second material to avoid any damage to the walls 3 and 6 resulting from a possible abnormal rise in their temperatures. Thus, the thickness of the cells 26 can be between 1 and 1.5 mm. The thicknesses of the sheets 20 and 23 have similar values.

Une variante de réalisation est représentée sur la figure 3, dans laquelle l'une des feuilles de la figure 20, a été remplacée parune feuille 120 ne comportant aucune dépression.An alternative embodiment is shown in Figure 3, in which one of the sheets of Figure 20 has been replaced by a sheet 120 having no depression.

Les lisières de contact de l'autre feuille 23 sont alors en contact avec la face intérieure 122 de la feuille 120. De manière analogue à ce qui a été précisé dans la description de la réalisation de la figure 2, les alvéoles ici délimitées entre la face 120 et les dépressions 24 de la feuille 23, par les lisières 25, sont emplies du même deuxième matériau que précédemment. Les feuilles 120 et 23 sont en outre réalisées dans le même premier matériau, généralement constitué par un super alliage résistant aux hautes températures.The contact edges of the other sheet 23 are then in contact with the inner face 122 of the sheet 120. In a manner similar to what has been specified in the description of the embodiment of FIG. 2, the cells here delimited between the face 120 and the depressions 24 of the sheet 23, by the selvedges 25, are filled with the same second material as above. The sheets 120 and 23 are also made of the same first material, generally consisting of a super alloy resistant to high temperatures.

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.

Notamment, s'il est nécessaire que les faces des parois 3, 6, qui délimitent la chambre de prémélange 4 soient réalisées dans ledit premier matériau résistant aux hautes températures, la face opposée a priori moins exposée aux températures élevées accidentelles, pourrait être réalisée en un matériau moins résistant. Dans les exemples décrits, les deux feuilles sont réalisées dans le même premier matériau.In particular, if it is necessary that the faces of the walls 3, 6, which delimit the premix chamber 4 are made of said first material resistant to high temperatures, the opposite face a priori less exposed to accidental high temperatures, could be made by a less resistant material. In the examples described, the two sheets are made of the same first material.

Claims (5)

1. Chambre de combustion, notamment pour turbo-machine, comprenant au moins un premier ensemble incluant un premier dispositif d'injection de carburant (11) et une première zone de combustion (16), et, adapté au fonctionnement de la chambre de combustion à un premier régime, tel que le régime de ralenti, et comprenant également au moins un deuxième ensemble incluant un deuxième dispositif d'injection de carburant (12) et une zone de prémélange (4) délimitée par des parois axiales (3, 6), ce deuxième ensemble étant muni de préférence en aval de la zone de prémélange (4) d'un dispositif de stabilisation de flamme (9) et étant adapté au fonctionnement de la chambre de combustion à un deuxième régime, tel que le régime à plein gaz, ladite zone de prémélange étant conçue pour un fonctionnement à une température déterminée, mais étant cependant susceptible d'être exposée pendant de brèves périodes à une température maximale supérieure à ladite température déterminée,
caractérisée en ce que lesdites parois axiales (3, 6) comportent, ménagées dans leur épaisseur, des alvéoles (26), dont au moins la face (20, 23 ; 120, 23) limitant la zone de prémélange (4) est constituée en un premier matériau résistant à ladite température maximale, et qui (les alvéoles) sont emplies d'un deuxième matériau, dont la température de fusion est comprise entre lesdites températures déterminée et maximale, et dont la chaleur latente de fusion est supérieure à 400 kiloJoule/kilogramme masse.1. Combustion chamber, in particular for a turbo-machine, comprising at least a first assembly including a first fuel injection device (11) and a first combustion zone (16), and, adapted to the operation of the combustion chamber at a first speed, such as the idling speed, and also comprising at least a second assembly including a second fuel injection device (12) and a premix zone (4) delimited by axial walls (3, 6) , this second assembly being preferably provided downstream of the premix zone (4) with a flame stabilization device (9) and being adapted to the operation of the combustion chamber at a second speed, such as at full speed gas, said premix zone being designed for operation at a determined temperature, but being however capable of being exposed for brief periods to a maximum temperature above said temperature determined erasure,
characterized in that said axial walls (3, 6) comprise, arranged in their thickness, cells (26), of which at least the face (20, 23; 120, 23) limiting the premix zone (4) is constituted by a first material resistant to said maximum temperature, and which (the cells) are filled with a second material, whose melting temperature is between said determined and maximum temperatures, and whose latent heat of fusion is greater than 400 kiloJoule / kilogram mass. 2. Chambre de combustion selon la revendication 1, caractérisée en ce que les parois axiales sont constituées par l'assemblage de deux feuilles (20, 23 ; 120, 23), comportant chacune une face d'assemblage, la face d'assemblage d'au moins l'une des deux feuilles comportant des dépressions (21, 24 ; 24) délimitées par des lisières de contact (22, 25 ; 25), qui sont en appui étanche sur la face d'assemblage de l'autre feuille, lesdites alvéoles (26) étant délimitées par les parties desdites faces d'assemblage qui comprennent les dépressions.2. Combustion chamber according to claim 1, characterized in that the axial walls are constituted by the assembly of two sheets (20, 23; 120, 23), each comprising an assembly face, the assembly face d '' at least one of the two sheets comprising depressions (21, 24; 24) delimited by contact selvedges (22, 25; 25), which are in leaktight support on the assembly face of the other sheet, said cells (26) being delimited by the parts of said assembly faces which include the depressions. 3. Chambre de combustion selon la revendication 2, caractérisée en ce que les deux feuilles sont maintenues assemblées par brasage desdites lisières de contact.3. Combustion chamber according to claim 2, characterized in that the two sheets are kept assembled by soldering said contact selvedges. 4. Chambre de combustion selon l'une quelconque des revendications 2 et 3, caractérisée en ce que chacune des deuxdites feuilles comporte des dépressions, qui sont regroupées par paire d'une dépression (21) d'une feuille (20) et d'une dépression (24) de l'autre feuille (23) pour former une alvéole (26).4. Combustion chamber according to any one of claims 2 and 3, characterized in that each of the two said sheets has depressions, which are grouped by pair of a depression (21) of a sheet (20) and of a depression (24) of the other sheet (23) to form a cell (26). 5. Chambre de combustion selon l'une quelconque des revendications 1 à 4, caractérisée en ce que le deuxième matériau est constitué par du chlorure de sodium.5. Combustion chamber according to any one of claims 1 to 4, characterized in that the second material consists of sodium chloride.
EP19930400907 1992-04-08 1993-04-07 Combustion chamber wall Expired - Lifetime EP0565442B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9204282 1992-04-08
FR9204282A FR2689965B1 (en) 1992-04-08 1992-04-08 Combustion chamber comprising at least two fuel injection assemblies.

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EP0565442B1 EP0565442B1 (en) 1996-06-05

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EP1813781A1 (en) * 2006-01-31 2007-08-01 Siemens Aktiengesellschaft Part of a turbine, turbine and operation method thereof
US20180266688A1 (en) * 2017-03-20 2018-09-20 United Technologies Corporation Impingement cooled components having integral thermal transfer features
US10627167B2 (en) * 2017-09-12 2020-04-21 General Electric Company Gas turbine engine having a heat absorption device utilizing phase change material
US11674396B2 (en) 2021-07-30 2023-06-13 General Electric Company Cooling air delivery assembly

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EP1813781A1 (en) * 2006-01-31 2007-08-01 Siemens Aktiengesellschaft Part of a turbine, turbine and operation method thereof
US20180266688A1 (en) * 2017-03-20 2018-09-20 United Technologies Corporation Impingement cooled components having integral thermal transfer features
EP3379149A1 (en) * 2017-03-20 2018-09-26 United Technologies Corporation Impingement cooled components having integral thermal transfer features
US10697635B2 (en) 2017-03-20 2020-06-30 Raytheon Technologies Corporation Impingement cooled components having integral thermal transfer features
US10627167B2 (en) * 2017-09-12 2020-04-21 General Electric Company Gas turbine engine having a heat absorption device utilizing phase change material
US11193720B2 (en) 2017-09-12 2021-12-07 General Electric Company Gas turbine engine having a heat absorption device and an associated method thereof
US11674396B2 (en) 2021-07-30 2023-06-13 General Electric Company Cooling air delivery assembly

Also Published As

Publication number Publication date
EP0565442B1 (en) 1996-06-05
FR2689965A1 (en) 1993-10-15
DE69302954T2 (en) 1996-11-28
FR2689965B1 (en) 1995-06-02
DE69302954D1 (en) 1996-07-11

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