EP0694739A1 - Double-walled combustor - Google Patents

Double-walled combustor Download PDF

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Publication number
EP0694739A1
EP0694739A1 EP95401667A EP95401667A EP0694739A1 EP 0694739 A1 EP0694739 A1 EP 0694739A1 EP 95401667 A EP95401667 A EP 95401667A EP 95401667 A EP95401667 A EP 95401667A EP 0694739 A1 EP0694739 A1 EP 0694739A1
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EP
European Patent Office
Prior art keywords
wall
combustion chamber
internal wall
external
space
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP95401667A
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German (de)
French (fr)
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EP0694739B1 (en
Inventor
Cristine Jeanne Marie Ambrogi
Serge Marcel Meunier
Denis Roger Henri Ansart
Denis Jean Maurice Sandelis
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA 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
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/20—Heat transfer, e.g. cooling
    • F05B2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/20—Heat transfer, e.g. cooling
    • F05B2260/202—Heat transfer, e.g. cooling by film cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/20—Heat transfer, e.g. cooling
    • F05B2260/221—Improvement of heat transfer
    • F05B2260/222—Improvement of heat transfer by creating turbulence

Definitions

  • combustion chamber furnaces fitted to these engines must be cooled accordingly, since their performance is increased the lower the air flow allocated to cooling them.
  • the combustion chambers are composed of double walls with interior tiles.
  • the use of tiles, made of ceramic materials, for example SiC / SiC, placed on the fireplace side poses cooling problems. Due to the low conductivity of the material, it is necessary to have a high cooling rate. It is also known that the temperatures become critical at the level of the ferrules arranged downstream of the chamber.
  • the present invention proposes new arrangements conducive to allowing cooling with limited flow rates, as well as the use of tiles without secondary drawbacks.
  • the subject of the invention is therefore a combustion chamber, usable in particular in a turbomachine, comprising at least one axial double wall, which itself has an internal wall traversed by a plurality of holes constituting a refrigeration multi-perforation and an outer wall spaced apart of the internal wall so as to provide a space for circulation of a coolant, said combustion chamber also comprising means for admitting said coolant inside said space.
  • the external face of the internal wall has multiple surface inequalities capable of promoting the evacuation of heat out of the material constituting said internal wall.
  • the main advantage of a combustion chamber according to the invention lies in the ability of its walls to withstand high temperatures thanks to an efficient evacuation of the heat which they receive.
  • the combustion chamber shown in FIG. 1 comprises a double external wall 1, of revolution, of axis 2; an internal double wall 3, of axis 2 revolution; a bottom 4 which connects, upstream, the two double walls 1 and 3 and extends transversely with respect to the axis 2; an outer casing 5, of axis 2, surrounding the inner double wall 1 and delimiting, in cooperation with this outer double wall 1, a first annular space 6; an internal envelope 7, disposed between the internal double wall 3 and the axis 2, of axis 2 revolution and delimiting, in cooperation with the internal double wall 3, a second annular space 8.
  • the combustion chamber also comprises two assemblies fuel injectors, shown diagrammatically in 9 and 10, supported by the bottom 4, connected to a device 11 for supplying fuel; an oxidant intake opening 12, generally air, for the admission of compressed oxidant into spaces 6 and 8, permanently communicating with said spaces 6 and 8, located upstream of the bottom 4; and a gas exhaust opening 13 outside the chamber 14 of the chamber, situated at the downstream limit of the chamber, for supplying gas to the blades of a gas turbine, itself situated downstream of the exhaust opening 13.
  • the enclosure 14 is delimited by the double external 1 and internal 3 walls and by the bottom 4 and opens downstream via the exhaust opening 13.
  • FIGS. 2 and 3 show more particularly the downstream part of the external double wall 1, located immediately upstream blades of the gas turbine, but the other parts of the double walls 1 and 3 are likely to have a similar constitution.
  • the external double wall 1 comprises a ferrule 15, of axis 2 revolution, which, by a V-shaped gutter 22 which is part of it, is connected to the downstream edge 16 of the external envelope 5.
  • the internal face 15A of the shell 15 constitutes the limit of the enclosure 14 of the combustion chamber.
  • a rim 17 of revolution of axis 2, integral with the ferrule 15, extends from the external face 15B of the ferrule 15, constituting a housing 18.
  • the support elements 20 hold the internal face 19A of the tile 19 separated from the external face 15B of the shell 15 so that a space 23 for circulation of a refrigerant fluid is formed between the tile 19 and the shell 15.
  • the external face 15B of the ferrule 15 has a rough surface, with a roughness Ra greater than 5, preferably close to 6.3 obtained either by sandblasting or by shot blasting of said external face 15B.
  • FIG. 3 includes all of the provisions of FIG. 2, supplemented by the production of a plurality of through holes 28, formed in the tile 19 and connecting the first annular space 6 to the space 23 between the tile 19 and the ferrule 15.
  • the compressed air contained in the first annular space 6 enters the annular space 23 by passing through the holes 24. Part of the air enters the enclosure 14 of the combustion chamber and , flowing along the internal face 15A of the ferrule 15, forms a film of refrigeration fluid of said ferrule. The rest of the fluid which has entered the space 23 escapes therefrom through the opening 25 and serves to cool the blades of the turbine (high pressure) contained in the enclosure 26.
  • the roughness of the external face 15B of the shell 15 prevents the formation of a flow-limiting layer of the refrigerant fluid along the external face 15B, which contributes to obtaining a large efficiency with regard to the evacuation of the heat and refrigeration of the shell 15.
  • the introduction of the refrigerant into the space 23, so that it strikes the roughness of the external face 15 of the shell, the tile 19 therefore being placed outside the enclosure 14 of the combustion chamber makes it possible to obtain said efficiency of the refrigeration.
  • the device 21 allows compensation for the differences in expansion between the shell 15 and the tile 19.
  • the arrangements in accordance with the invention are applicable to the various axial walls of the combustion chamber and, firstly, to that which is thermally most exposed, which is located in the downstream part, adjacent to the enclosure of the turbine. gas proper.
  • the adoption of the described measures has the effect of reducing the temperature from 40 to 50 ° C, but also a gain in mass, because it makes it possible to produce the tiles 19 in a material having a low density (such as materials composites or the like) and capable of withstanding temperatures of the order of 700 ° C.

Abstract

The chamber has a double axial wall perforated by a number of holes (27) which define a cooling flow for the outer (19) of the two wall portions. Together with the inner portion (15), the outer portion defines a space (23) in which a cooling fluid circulates. The outer face (15B) of the inner wall portion has a roughened surface created by grinding or sand-blasting. The roughness of the inner wall portion's outer surface is of the order of 6.3 Ra. The inner wall portion is formed as a single annular component, while the outer wall portion is formed by a series of tiles attached to the inner portion by spacers (21) which compensate for thermal expansion of the components. <IMAGE>

Description

Les turboréacteurs civils et militaires tendent vers des taux de compression de plus en plus élevés, d'où une élévation des températures en sortie de compresseur haute pression et à l'entrée de la turbine haute pression.Civil and military turbojet engines tend towards higher and higher compression rates, resulting in higher temperatures at the outlet of the high pressure compressor and at the inlet of the high pressure turbine.

Les foyers de chambres de combustion équipant ces moteurs doivent être refroidis en conséquence, car leurs performances sont d'autant augmentées que le débit d'air alloué à leur refroidissement est faible.The combustion chamber furnaces fitted to these engines must be cooled accordingly, since their performance is increased the lower the air flow allocated to cooling them.

Actuellement, les chambres de combustion sont composées de double parois à tuiles intérieures. Cependant, l'utilisation de tuiles, en matériaux céramiques, par exemple SiC/SiC, placées côté foyer pose des problèmes de refroidissement. Du fait de la faible conductivité du matériau, il est nécessaire d'avoir un grand débit de refroidissement. On sait également que les températures deviennent critiques au niveau des viroles disposées en aval de la chambre.Currently, the combustion chambers are composed of double walls with interior tiles. However, the use of tiles, made of ceramic materials, for example SiC / SiC, placed on the fireplace side poses cooling problems. Due to the low conductivity of the material, it is necessary to have a high cooling rate. It is also known that the temperatures become critical at the level of the ferrules arranged downstream of the chamber.

Il est donc impératif de prévoir une technologique de refroidissement efficace qui limite le débit d'air nécessaire à ce refroidissement.It is therefore imperative to provide an efficient cooling technology which limits the air flow required for this cooling.

La présente invention propose de nouvelles dispositions propices à permettre un refroidissement avec des débits limités, ainsi que l'utilisation de tuiles sans inconvénients secondaires.The present invention proposes new arrangements conducive to allowing cooling with limited flow rates, as well as the use of tiles without secondary drawbacks.

L'invention a donc pour objet une chambre de combustion, utilisable notamment dans une turbomachine, comportant au moins une double paroi axiale, qui comporte elle-même une paroi interne traversée par une pluralité de trous constituant une multiperforation de réfrigération et une paroi externe écartée de la paroi interne de manière à ménager un espace de circulation d'un fluide réfrigérant, ladite chambre de combustion comportant également des moyens d'admission dudit fluide réfrigérant à l'intérieur dudit espace.The subject of the invention is therefore a combustion chamber, usable in particular in a turbomachine, comprising at least one axial double wall, which itself has an internal wall traversed by a plurality of holes constituting a refrigeration multi-perforation and an outer wall spaced apart of the internal wall so as to provide a space for circulation of a coolant, said combustion chamber also comprising means for admitting said coolant inside said space.

Selon l'invention, la face externe de la paroi interne présente de multiples inégalités de surface aptes à favoriser l'évacuation de la chaleur hors du matériau constituant ladite paroi interne.According to the invention, the external face of the internal wall has multiple surface inequalities capable of promoting the evacuation of heat out of the material constituting said internal wall.

Les avantageuses dispositions suivantes sont en outre de préférence adoptées:

  • lesdites irrégularités de surface sont obtenues par grenaillage ou par sablage de la face externe de la paroi interne, de manière à obtenir une rugosité Ra supérieure à 5, de préférence voisine de 6,3;
  • la paroi interne comprend une virole annulaire, cependant que la paroi externe comprend plusieurs tuiles montées sur ladite paroi interne au moyen notamment de dispositifs compensateurs de dilatation thermique;
  • la paroi interne comporte des rebords annulaires qui sont disposés en saillie par rapport à la face externe de cette paroi interne, cependant que la paroi externe comprend des tuiles ayant des bords amont qui sont montés sur la paroi interne notamment au moyen desdits rebords annulaires et qui sont munis d'orifices d'admission, dans l'espace séparant les parois interne et externe, du fluide réfrigérant;
  • la paroi externe est traversée par une pluralité de trous constituant une multiperforation de réfrigération;
  • elle est associée à une turbine à gaz disposée en aval, possédant une enceinte de turbine à gaz, cependant que la partie aval de ladite double paroi de la chambre de combustion comporte des passages reliant l'espace compris entre les deux dites parois à l'enceinte de turbine à gaz, de manière qu'une partie du fluide réfrigérant admis dans ledit espace soit évacuée à l'intérieur de ladite enceinte de turbine à gaz.
The following advantageous arrangements are also preferably adopted:
  • said surface irregularities are obtained by shot blasting or by sandblasting of the external face of the internal wall, so as to obtain a roughness Ra greater than 5, preferably close to 6.3;
  • the internal wall comprises an annular ring, while the external wall comprises several tiles mounted on said internal wall by means in particular of thermal expansion compensating devices;
  • the internal wall has annular edges which are arranged projecting with respect to the external face of this internal wall, while the external wall comprises tiles having upstream edges which are mounted on the internal wall in particular by means of said annular edges and which are provided with intake orifices, in the space separating the internal and external walls, of the refrigerant;
  • the external wall is traversed by a plurality of holes constituting a refrigeration multi-perforation;
  • it is associated with a gas turbine arranged downstream, having a gas turbine enclosure, while the downstream part of said double wall of the combustion chamber has passages connecting the space between the two said walls to the gas turbine enclosure, so that part of the refrigerant admitted into said space is evacuated inside said gas turbine enclosure.

L'avantage principal d'une chambre de combustion conforme à l'invention réside dans l'aptitude de ses parois à supporter des températures élevées grâce à une évacuation efficace de la chaleur qu'elles reçoivent.The main advantage of a combustion chamber according to the invention lies in the ability of its walls to withstand high temperatures thanks to an efficient evacuation of the heat which they receive.

L'invention sera mieux comprise et des caractéristiques secondaires et leurs avantages apparaîtront au cours de la description qui suit de réalisations donnée ci-dessous à titre d'exemple.The invention will be better understood and secondary characteristics and their advantages will become apparent during the following 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; et
  • les figures 2 et 3 sont des agrandissements du détail de la figure 1 représentant une partie aval de la paroi de la chambre de combustion, selon deux réalisations différentes conformes à l'invention.
Reference will be made to the appended drawings in which:
  • Figure 1 is an axial section of a combustion chamber according to the invention; and
  • Figures 2 and 3 are enlargements of the detail of Figure 1 showing a downstream part of the wall of the combustion chamber, according to two different embodiments according to the invention.

La chambre de combustion représentée sur la figure 1 comprend une double paroi externe 1, de révolution, d'axe 2 ; une double paroi interne 3, de révolution d'axe 2 ; un fond 4 qui relie, en amont, les deux double parois 1 et 3 et s'étend transversalement par rapport à l'axe 2 ; une enveloppe externe 5, d'axe 2, entourant la double paroi interne 1 et délimitant, en coopération avec cette double paroi externe 1, un premier espace annulaire 6 ; une enveloppe interne 7, disposée entre la double paroi interne 3 et l'axe 2, de révolution d'axe 2 et délimitant, en coopération avec la double paroi interne 3, un deuxième espace annulaire 8. La chambre de combustion comporte également deux ensembles d'injecteurs de carburant, schématisés en 9 et 10, supportés par le fond 4, raccordés à un dispositif 11 d'alimentation en carburant; une ouverture d'admission 12 de comburant, généralement de l'air, pour l'admission de comburant comprimé dans les espaces 6 et 8, communiquant en permanence avec lesdits espaces 6 et 8, située en amont du fond 4 ; et une ouverture d'échappement 13 des gaz hors de l'enceinte 14 de la chambre, située à la limite aval de la chambre, pour alimenter en gaz les aubages d'une turbine à gaz, elle-même située en aval de l'ouverture d'échappement 13. L'enceinte 14 est délimitée par les double parois externe 1 et interne 3 et par le fond 4 et débouche en aval par l'intermédiaire de l'ouverture d'échappement 13.The combustion chamber shown in FIG. 1 comprises a double external wall 1, of revolution, of axis 2; an internal double wall 3, of axis 2 revolution; a bottom 4 which connects, upstream, the two double walls 1 and 3 and extends transversely with respect to the axis 2; an outer casing 5, of axis 2, surrounding the inner double wall 1 and delimiting, in cooperation with this outer double wall 1, a first annular space 6; an internal envelope 7, disposed between the internal double wall 3 and the axis 2, of axis 2 revolution and delimiting, in cooperation with the internal double wall 3, a second annular space 8. The combustion chamber also comprises two assemblies fuel injectors, shown diagrammatically in 9 and 10, supported by the bottom 4, connected to a device 11 for supplying fuel; an oxidant intake opening 12, generally air, for the admission of compressed oxidant into spaces 6 and 8, permanently communicating with said spaces 6 and 8, located upstream of the bottom 4; and a gas exhaust opening 13 outside the chamber 14 of the chamber, situated at the downstream limit of the chamber, for supplying gas to the blades of a gas turbine, itself situated downstream of the exhaust opening 13. The enclosure 14 is delimited by the double external 1 and internal 3 walls and by the bottom 4 and opens downstream via the exhaust opening 13.

Chaque double paroi est réalisée selon l'une ou l'autre des variantes représentées sur les figures 2 et 3. En l'espèce, les figures 2 et 3 représentent plus particulièrement la partie aval de la double paroi externe 1, située immédiatement en amont des aubages de la turbine à gaz, mais les autres parties des double parois 1 et 3 sont susceptibles de posséder une constitution analogue.Each double wall is produced according to one or other of the variants represented in FIGS. 2 and 3. In the present case, FIGS. 2 and 3 show more particularly the downstream part of the external double wall 1, located immediately upstream blades of the gas turbine, but the other parts of the double walls 1 and 3 are likely to have a similar constitution.

Dans la réalisation de la figure 2, la double paroi externe 1 comprend une virole 15, de révolution d'axe 2, qui, par une gouttière 22 en V qui en fait partie, est raccordée à la lisière aval 16 de l'enveloppe externe 5. La face interne 15A de la virole 15 constitue la limite de l'enceinte 14 de la chambre de combustion. De place en place, un rebord 17 de révolution d'axe 2, solidaire de la virole 15, s'étend à partir de la face externe 15B de la virole 15, en constituant un logement 18. Une tuile 19, présentant des éléments d'appui 20 sur la face externe 15B de la virole 15, a son extrémité amont 19A introduite à coulissement dans le logement 18 et y est maintenue par l'intermédiaire d'un dispositif de montage 21, et à son extrémité aval 19B en appui, et fixée sur la gouttière 22. Les éléments d'appui 20 maintiennent la face interne 19A de la tuile 19 écartée de la face externe 15B de la virole 15 de sorte qu'un espace 23 de circulation d'un fluide réfrigérant est ménagé entre la tuile 19 et la virole 15.In the embodiment of FIG. 2, the external double wall 1 comprises a ferrule 15, of axis 2 revolution, which, by a V-shaped gutter 22 which is part of it, is connected to the downstream edge 16 of the external envelope 5. The internal face 15A of the shell 15 constitutes the limit of the enclosure 14 of the combustion chamber. From place to place, a rim 17 of revolution of axis 2, integral with the ferrule 15, extends from the external face 15B of the ferrule 15, constituting a housing 18. A tile 19, having elements of support 20 on the external face 15B of the ferrule 15, at its upstream end 19A slidably introduced into the housing 18 and is held there by means of a mounting device 21, and at its downstream end 19B in support, and fixed on the gutter 22. The support elements 20 hold the internal face 19A of the tile 19 separated from the external face 15B of the shell 15 so that a space 23 for circulation of a refrigerant fluid is formed between the tile 19 and the shell 15.

L'espace 23 communique :

  • par l'intermédiaire de trous 24 ménagés dans le rebord 17 avec le premier espace annulaire 6;
  • par l'intermédiaire d'une ouverture 25 ménagée dans la paroi de la gouttière 22, avec l'enceinte 26 de la turbine à gaz; et
  • par l'intermédiaire d'une pluralité de petits trous traversants 27, ménagés dans la paroi de la virole 15, avec l'enceinte 14 de la chambre de combustion.
Space 23 communicates:
  • by means of holes 24 made in the rim 17 with the first annular space 6;
  • through an opening 25 formed in the wall of the gutter 22, with the enclosure 26 of the gas turbine; and
  • by means of a plurality of small through holes 27, formed in the wall of the shell 15, with the enclosure 14 of the combustion chamber.

A noter encore le fait que la face externe 15B de la virole 15 a une surface rugueuse, d'une rugosité Ra supérieure à 5, de préférence voisine de 6,3 obtenue soit par sablage, soit par grenaillage de ladite face externe 15B.Note also the fact that the external face 15B of the ferrule 15 has a rough surface, with a roughness Ra greater than 5, preferably close to 6.3 obtained either by sandblasting or by shot blasting of said external face 15B.

La réalisation de la figure 3 comporte l'ensemble des dispositions de la figure 2, complété par la réalisation d'une pluralité de trous traversants 28, ménagés dans la tuile 19 et reliant le premier espace annulaire 6 à l'espace 23 compris entre la tuile 19 et la virole 15. Les trous 28, comme les trous 27, forment des multiperforations de leurs parois respectives.The embodiment of FIG. 3 includes all of the provisions of FIG. 2, supplemented by the production of a plurality of through holes 28, formed in the tile 19 and connecting the first annular space 6 to the space 23 between the tile 19 and the ferrule 15. The holes 28, like the holes 27, form multiperforations of their respective walls.

Selon la réalisation de la figure 2, l'air comprimé contenu dans le premier espace annulaire 6 pénètre dans l'espace annulaire 23 en traversant les trous 24. Une partie de l'air pénètre dans l'enceinte 14 de la chambre de combustion et, en s'écoulant le long de la face interne 15A de la virole 15, forme un film de fluide de réfrigération de ladite virole. Le reste du fluide ayant pénétré dans l'espace 23 s'en échappe en traversant l'ouverture 25 et sert à refroidir les aubages de la turbine (haute pression) contenus dans l'enceinte 26.According to the embodiment of FIG. 2, the compressed air contained in the first annular space 6 enters the annular space 23 by passing through the holes 24. Part of the air enters the enclosure 14 of the combustion chamber and , flowing along the internal face 15A of the ferrule 15, forms a film of refrigeration fluid of said ferrule. The rest of the fluid which has entered the space 23 escapes therefrom through the opening 25 and serves to cool the blades of the turbine (high pressure) contained in the enclosure 26.

Il convient d'observer que la rugosité de la face externe 15B de la virole 15 empêche la formation d'une couche limite d'écoulement du fluide réfrigérant le long de la face externe 15B, ce qui contribue à l'obtention d'une grande efficacité en ce qui concerne l'évacuation de la chaleur et la réfrigération de la virole 15. L'introduction du réfrigérant dans l'espace 23, de manière qu'il frappe les aspérités de la face externe 15 de la virole, la tuile 19 étant donc placée à l'extérieur de l'enceinte 14 de la chambre de combustion permet l'obtention de ladite efficacité de la réfrigération.It should be observed that the roughness of the external face 15B of the shell 15 prevents the formation of a flow-limiting layer of the refrigerant fluid along the external face 15B, which contributes to obtaining a large efficiency with regard to the evacuation of the heat and refrigeration of the shell 15. The introduction of the refrigerant into the space 23, so that it strikes the roughness of the external face 15 of the shell, the tile 19 therefore being placed outside the enclosure 14 of the combustion chamber makes it possible to obtain said efficiency of the refrigeration.

Le dispositif 21 permet la compensation des différences de dilatation entre la virole 15 et la tuile 19.The device 21 allows compensation for the differences in expansion between the shell 15 and the tile 19.

Les dispositions conformes à l'invention sont applicables aux diverses parois axiales de la chambre de combustion et, en premier lieu, à celle qui est thermiquement la plus exposée, qui est située dans la partie aval, adjacente à l'enceinte de la turbine à gaz proprement dite. L'adoption des dispositions décrites a pour effet une diminution de la température de 40 à 50°C, mais aussi un gain de masse, car elle rend possible la réalisation des tuiles 19 en un matériau ayant une faible masse volumique (tel que des matériaux composites ou analogues) et apte à résister à des températures de l'ordre de 700°C.The arrangements in accordance with the invention are applicable to the various axial walls of the combustion chamber and, firstly, to that which is thermally most exposed, which is located in the downstream part, adjacent to the enclosure of the turbine. gas proper. The adoption of the described measures has the effect of reducing the temperature from 40 to 50 ° C, but also a gain in mass, because it makes it possible to produce the tiles 19 in a material having a low density (such as materials composites or the like) and capable of withstanding temperatures of the order of 700 ° C.

En outre, les fuites de gaz chauds qui, antérieurement, se produisaient au niveau des tuiles placées entre la virole et l'axe, sont éliminées, lesdites tuiles étant maintenant placées à l'extérieur de l'enceinte 14 de la chambre de combustion, au-delà de la virole continue 15 par rapport à l'axe 2.In addition, the hot gas leaks which previously occurred at the level of the tiles placed between the shell and the axis, are eliminated, said tiles now being placed outside the enclosure 14 of the combustion chamber, beyond the continuous shell 15 relative to the axis 2.

Enfin, la récupération de la partie du fluide réfrigérant, qui est évacuée dans l'enceinte 26 de la turbine à gaz, contribue à l'obtention d'un rendement élevé de la turbomachine.Finally, the recovery of the part of the refrigerant, which is discharged into the enclosure 26 of the gas turbine, contributes to obtaining a high efficiency of the turbomachine.

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 (8)

Chambre de combustion, utilisable notamment dans une turbomachine, comportant au moins une double paroi axiale (1;3) qui comporte elle-même une paroi interne (15) traversée par une pluralité de trous (27) constituant une multiperforation de réfrigération et une paroi externe (19) écartée de la paroi interne (15) de manière à ménager un espace (23) de circulation d'un fluide réfrigérant, ladite chambre de combustion comportant également des moyens (12-6-8) d'admission dudit fluide réfrigérant à l'intérieur dudit espace, ladite face externe (15B) de la paroi interne (15) présentant de multiples inégalités de surface aptes à favoriser l'évacuation de la chaleur hors du matériau constituant ladite paroi interne, caractérisée en ce que lesdites irrégularités de surface sont obtenues par projection de particules sur la face externe de la paroi interne.Combustion chamber, usable in particular in a turbomachine, comprising at least one axial double wall (1; 3) which itself comprises an internal wall (15) traversed by a plurality of holes (27) constituting a refrigeration multi-perforation and a wall external (19) spaced from the internal wall (15) so as to provide a space (23) for the circulation of a coolant, said combustion chamber also comprising means (12-6-8) for admitting said coolant inside said space, said external face (15B) of the internal wall (15) having multiple surface inequalities capable of promoting the evacuation of heat from the material constituting said internal wall, characterized in that said irregularities of surface are obtained by projection of particles on the external face of the internal wall. Chambre de combustion selon la revendication 1, caractérisée en ce que la projection est obtenue par grenaillage.Combustion chamber according to claim 1, characterized in that the projection is obtained by shot blasting. Chambre de combustion selon la revendication 1, caractérisée en ce que la projection est obtenue par sablageCombustion chamber according to claim 1, characterized in that the projection is obtained by sandblasting Chambre de combustion selon l'une quelconque des revendications 1 à 3, caractérisée en ce que la rugosité Ra de la face externe de la paroi interne est supérieure à 5, de préférence voisine de 6,3.Combustion chamber according to any one of claims 1 to 3, characterized in that the roughness Ra of the external face of the internal wall is greater than 5, preferably close to 6.3. Chambre de combustion selon l'une quelconque des revendications 1 à 4, caractérisée en ce que la paroi interne (15) comprend une virole annulaire, cependant que la paroi externe (19) comprend plusieurs tuiles montées sur ladite paroi interne au moyen notamment de dispositifs (21) compensateurs de dilatation thermique.Combustion chamber according to any one of claims 1 to 4, characterized in that the internal wall (15) comprises an annular ring, while the external wall (19) comprises several tiles mounted on said internal wall by means in particular of devices (21) thermal expansion compensators. Chambre de combustion selon l'une quelconque des revendications 1 à 5, caractérisée en ce que la paroi interne (15) comporte des rebords annulaires (17) qui sont disposés en saillie par rapport à la face externe (15B) de cette paroi interne, cependant que la paroi externe (19) comprend des tuiles ayant des bords amont (19A) qui sont montés sur la paroi interne notamment au moyen desdits rebords annulaires (17) et qui sont munis d'orifices d'admission (24) dans l'espace (23) séparant les parois interne (15) et externe (19) du fluide réfrigérant.Combustion chamber according to any one of Claims 1 to 5, characterized in that the internal wall (15) has annular flanges (17) which are arranged projecting relative to the external face (15B) of this internal wall, however that the external wall (19) comprises tiles having upstream edges (19A) which are mounted on the internal wall in particular by means of said annular flanges (17) and which are provided with inlet orifices (24) in the space (23) separating the internal (15) and external (19) walls of the refrigerant. Chambre de combustion selon l'une quelconque des revendications 1 à 6, caractérisée en ce que la paroi externe (19) est traversée par une pluralité de trous (28) constituant une multiperforation de réfrigération.Combustion chamber according to any one of Claims 1 to 6, characterized in that the external wall (19) is traversed by a plurality of holes (28) constituting a refrigeration multi-perforation. Chambre de combustion selon l'une quelconque des revendications 1 à 7, caractérisée en ce qu'elle est associée à une turbine à gaz disposée en aval, possédant une enceinte (26) de turbine à gaz, cependant que la partie aval (22) de ladite double paroi de la chambre de combustion comporte des passages (25) reliant l'espace (23) compris entre les deux dites parois à l'enceinte (26) de turbine à gaz, de manière qu'une partie du fluide réfrigérant admis dans ledit espace soit évacuée à l'intérieur de ladite enceinte (26) de turbine à gaz.Combustion chamber according to any one of claims 1 to 7, characterized in that it is associated with a downstream gas turbine, having a gas turbine enclosure (26), while the downstream part (22) of said double wall of the combustion chamber has passages (25) connecting the space (23) between the two said walls to the enclosure (26) of the gas turbine, so that part of the refrigerant admitted in said space is evacuated inside said enclosure (26) of a gas turbine.
EP95401667A 1994-07-27 1995-07-12 Double-walled combustor Expired - Lifetime EP0694739B1 (en)

Applications Claiming Priority (2)

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FR9409277A FR2723177B1 (en) 1994-07-27 1994-07-27 COMBUSTION CHAMBER COMPRISING A DOUBLE WALL
FR9409277 1994-07-27

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EP0694739A1 true EP0694739A1 (en) 1996-01-31
EP0694739B1 EP0694739B1 (en) 1998-09-30

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19727407A1 (en) * 1997-06-27 1999-01-07 Siemens Ag Gas-turbine combustion chamber heat shield with cooling arrangement
EP0905353A1 (en) * 1997-09-30 1999-03-31 Abb Research Ltd. Impingement cooled wall element
FR2970065A1 (en) * 2011-01-03 2012-07-06 Gen Electric COMBUSTION DEVICE FOR TURBINE ENGINE
WO2014019754A1 (en) * 2012-08-02 2014-02-06 Siemens Aktiengesellschaft Combustion chamber cooling

Families Citing this family (35)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5782294A (en) * 1995-12-18 1998-07-21 United Technologies Corporation Cooled liner apparatus
FR2752916B1 (en) * 1996-09-05 1998-10-02 Snecma THERMAL PROTECTIVE SHIRT FOR TURBOREACTOR COMBUSTION CHAMBER
DE19745683A1 (en) * 1997-10-16 1999-04-22 Bmw Rolls Royce Gmbh Suspension of an annular gas turbine combustion chamber
FR2770283B1 (en) * 1997-10-29 1999-11-19 Snecma COMBUSTION CHAMBER FOR TURBOMACHINE
US6079199A (en) * 1998-06-03 2000-06-27 Pratt & Whitney Canada Inc. Double pass air impingement and air film cooling for gas turbine combustor walls
US6536201B2 (en) * 2000-12-11 2003-03-25 Pratt & Whitney Canada Corp. Combustor turbine successive dual cooling
US6701714B2 (en) * 2001-12-05 2004-03-09 United Technologies Corporation Gas turbine combustor
FR2840974B1 (en) * 2002-06-13 2005-12-30 Snecma Propulsion Solide SEAL RING FOR COMBUSTION CAHMBERS AND COMBUSTION CHAMBER COMPRISING SUCH A RING
US6964170B2 (en) * 2003-04-28 2005-11-15 Pratt & Whitney Canada Corp. Noise reducing combustor
US7464554B2 (en) * 2004-09-09 2008-12-16 United Technologies Corporation Gas turbine combustor heat shield panel or exhaust panel including a cooling device
US7219498B2 (en) 2004-09-10 2007-05-22 Honeywell International, Inc. Waffled impingement effusion method
ITMI20041779A1 (en) * 2004-09-17 2004-12-17 Nuovo Pignone Spa PROTECTION DEVICE OF A STATOR OF A TURBINE
US7237389B2 (en) * 2004-11-18 2007-07-03 Siemens Power Generation, Inc. Attachment system for ceramic combustor liner
GB2420614B (en) * 2004-11-30 2009-06-03 Alstom Technology Ltd Tile and exo-skeleton tile structure
US7628020B2 (en) * 2006-05-26 2009-12-08 Pratt & Whitney Canada Cororation Combustor with improved swirl
US7856830B2 (en) * 2006-05-26 2010-12-28 Pratt & Whitney Canada Corp. Noise reducing combustor
US7788926B2 (en) * 2006-08-18 2010-09-07 Siemens Energy, Inc. Resonator device at junction of combustor and combustion chamber
DE102007018061A1 (en) 2007-04-17 2008-10-23 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine combustion chamber wall
FR2920525B1 (en) * 2007-08-31 2014-06-13 Snecma SEPARATOR FOR SUPPLYING THE COOLING AIR OF A TURBINE
US20100095680A1 (en) * 2008-10-22 2010-04-22 Honeywell International Inc. Dual wall structure for use in a combustor of a gas turbine engine
US20100095679A1 (en) * 2008-10-22 2010-04-22 Honeywell International Inc. Dual wall structure for use in a combustor of a gas turbine engine
US9145779B2 (en) * 2009-03-12 2015-09-29 United Technologies Corporation Cooling arrangement for a turbine engine component
US20100257863A1 (en) * 2009-04-13 2010-10-14 General Electric Company Combined convection/effusion cooled one-piece can combustor
EP2489836A1 (en) * 2011-02-21 2012-08-22 Karlsruher Institut für Technologie Coolable component
US8904802B2 (en) * 2011-06-30 2014-12-09 General Electric Company Turbomachine combustor assembly including a vortex modification system
US20130067932A1 (en) * 2011-09-20 2013-03-21 Honeywell International Inc. Combustion sections of gas turbine engines with convection shield assemblies
JP5821550B2 (en) 2011-11-10 2015-11-24 株式会社Ihi Combustor liner
US9657949B2 (en) * 2012-10-15 2017-05-23 Pratt & Whitney Canada Corp. Combustor skin assembly for gas turbine engine
US9518739B2 (en) 2013-03-08 2016-12-13 Pratt & Whitney Canada Corp. Combustor heat shield with carbon avoidance feature
WO2014149108A1 (en) 2013-03-15 2014-09-25 Graves Charles B Shell and tiled liner arrangement for a combustor
US10100737B2 (en) 2013-05-16 2018-10-16 Siemens Energy, Inc. Impingement cooling arrangement having a snap-in plate
EP3149284A2 (en) * 2014-05-29 2017-04-05 General Electric Company Engine components with impingement cooling features
DE102016222099A1 (en) 2016-11-10 2018-05-17 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber of a gas turbine
GB201720254D0 (en) * 2017-12-05 2018-01-17 Rolls Royce Plc A combustion chamber arrangement
EP3848556A1 (en) * 2020-01-13 2021-07-14 Ansaldo Energia Switzerland AG Gas turbine engine having a transition piece with inclined cooling holes

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB636811A (en) * 1948-05-05 1950-05-10 Lucas Ltd Joseph Improvements relating to combustion chambers for prime movers
GB636818A (en) * 1948-05-05 1950-05-10 George Oulianoff Improvements relating to gas-turbine engine parts
US4392355A (en) * 1969-11-13 1983-07-12 General Motors Corporation Combustion liner
EP0248731A1 (en) * 1986-06-04 1987-12-09 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Gas turbine combustion chamber having mixing orifices which assure the positioning of a hot wall on a cool wall
EP0321320A1 (en) * 1987-12-16 1989-06-21 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbine combustion chamber having a double-walled connection part
FR2624954A1 (en) * 1987-12-18 1989-06-23 Rolls Royce Plc COMBUSTION CHAMBER STRUCTURE FOR A GAS TURBINE ENGINE
WO1992016798A1 (en) * 1991-03-22 1992-10-01 Rolls-Royce Plc Gas turbine engine combustor
US5201847A (en) * 1991-11-21 1993-04-13 Westinghouse Electric Corp. Shroud design

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR321320A (en) * 1902-05-20 1903-01-07 Pharmacie Centrale De France New hot air sprayer
US3744242A (en) * 1972-01-25 1973-07-10 Gen Motors Corp Recirculating combustor
US4233123A (en) * 1978-12-18 1980-11-11 General Motors Corporation Method for making an air cooled combustor
US4944152A (en) * 1988-10-11 1990-07-31 Sundstrand Corporation Augmented turbine combustor cooling
US5065817A (en) * 1988-10-14 1991-11-19 Mile High Equipment Company Auger type ice flaking machine with enhanced heat transfer capacity evaporator/freezing section

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB636811A (en) * 1948-05-05 1950-05-10 Lucas Ltd Joseph Improvements relating to combustion chambers for prime movers
GB636818A (en) * 1948-05-05 1950-05-10 George Oulianoff Improvements relating to gas-turbine engine parts
US4392355A (en) * 1969-11-13 1983-07-12 General Motors Corporation Combustion liner
EP0248731A1 (en) * 1986-06-04 1987-12-09 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Gas turbine combustion chamber having mixing orifices which assure the positioning of a hot wall on a cool wall
EP0321320A1 (en) * 1987-12-16 1989-06-21 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbine combustion chamber having a double-walled connection part
FR2624954A1 (en) * 1987-12-18 1989-06-23 Rolls Royce Plc COMBUSTION CHAMBER STRUCTURE FOR A GAS TURBINE ENGINE
WO1992016798A1 (en) * 1991-03-22 1992-10-01 Rolls-Royce Plc Gas turbine engine combustor
US5201847A (en) * 1991-11-21 1993-04-13 Westinghouse Electric Corp. Shroud design

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19727407A1 (en) * 1997-06-27 1999-01-07 Siemens Ag Gas-turbine combustion chamber heat shield with cooling arrangement
EP0905353A1 (en) * 1997-09-30 1999-03-31 Abb Research Ltd. Impingement cooled wall element
FR2970065A1 (en) * 2011-01-03 2012-07-06 Gen Electric COMBUSTION DEVICE FOR TURBINE ENGINE
CN102589006A (en) * 2011-01-03 2012-07-18 通用电气公司 Combustor assemblies for use in turbine engines and methods of assembling same
CN102589006B (en) * 2011-01-03 2016-06-22 通用电气公司 Combusting room device and assemble method thereof for turbogenerator
WO2014019754A1 (en) * 2012-08-02 2014-02-06 Siemens Aktiengesellschaft Combustion chamber cooling

Also Published As

Publication number Publication date
DE69505067D1 (en) 1998-11-05
EP0694739B1 (en) 1998-09-30
FR2723177A1 (en) 1996-02-02
DE69505067T2 (en) 1999-04-08
FR2723177B1 (en) 1996-09-06
US5598697A (en) 1997-02-04

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