EP0248731B1 - Gas turbine combustion chamber having mixing orifices which assure the positioning of a hot wall on a cool wall - Google Patents

Gas turbine combustion chamber having mixing orifices which assure the positioning of a hot wall on a cool wall Download PDF

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Publication number
EP0248731B1
EP0248731B1 EP87401235A EP87401235A EP0248731B1 EP 0248731 B1 EP0248731 B1 EP 0248731B1 EP 87401235 A EP87401235 A EP 87401235A EP 87401235 A EP87401235 A EP 87401235A EP 0248731 B1 EP0248731 B1 EP 0248731B1
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EP
European Patent Office
Prior art keywords
wall
hot
cold
combustion chamber
hot wall
Prior art date
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Expired
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EP87401235A
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German (de)
French (fr)
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EP0248731A1 (en
Inventor
Gérard Yves Georges Barbier
Gérard Joseph Pascal Bayle-Laboure
Michel André Albert Desaulty
François Duchene
Pascal Maurice Trouillot
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Safran Aircraft Engines SAS
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Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04Air inlet arrangements
    • F23R3/045Air inlet arrangements using pipes
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002Wall structures
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04Air inlet arrangements
    • F23R3/06Arrangement of apertures along the flame tube
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05BINDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00Function
    • F05B2260/20Heat transfer, e.g. cooling
    • F05B2260/201Heat transfer, e.g. cooling by impingement of a fluid
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05BINDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00Function
    • F05B2260/20Heat transfer, e.g. cooling
    • F05B2260/202Heat transfer, e.g. cooling by film cooling

Definitions

  • the present invention relates to combustion chambers and more particularly to double-walled chambers, in particular for turbomachines comprising at least one outer wall, known as a cold wall, formed of several mechanically welded ferrules and intended to ensure the mechanical rigidity of the combustion chamber, and comprising at least one inner wall, called the hot wall intended to ensure the thermal resistance of the chamber, formed of several successive ferrules assembled together and on the cold wall so as to leave free between the two walls a cooling space allowing a set of dilation of the hot wall; the chamber also comprising mixing orifices passing through the two walls to allow the introduction of primary combustion and dilution air inside the chamber.
  • at least one outer wall known as a cold wall
  • the hot wall intended to ensure the thermal resistance of the chamber, formed of several successive ferrules assembled together and on the cold wall so as to leave free between the two walls a cooling space allowing a set of dilation of the hot wall
  • the chamber also comprising mixing orifices passing through the two walls to allow the introduction of primary combustion and
  • Cooling uses the thermal shield effect provided by secondary air inlets creating along the internal surface of the wall a parietal layer avoiding direct contact between the wall and the combustion gases. This layer which dilutes as it travels from upstream to downstream must be renewed by means of air inlets successively distributed in the length of the chamber.
  • US Pat. No. 4,302,941 provides an interior wall, of which stepped hot rings are fixed with radial clearance by screws on the cold wall, while tongues integral with the external face of the hot rings ensure the guiding of the convection air and limit the radial clearance.
  • these tabs useful for channeling the convection air, create significant wakes in the parietal film formed at the outlet of the hot shell, which disturbs the effectiveness of this film.
  • the dilution air inlet orifices placed directly at the outlet of the film also disturb the latter.
  • Patent FR 2 023 415 provides a combustion chamber with double walls, the internal rings of the hot wall being stepped and fixed by their upstream edge, while the downstream comprises pads for limiting the expansion play of the ring.
  • One annoyance presented by this type of chamber which uses the principle of cooling by co-current convection and by parietal film is to present a film thickness which is not completely controlled in function of the expansion of the hot wall.
  • Another drawback lies in the fact that, as in the previous device, the downstream clearance limitation pads introduce wakes in the parietal film, wakes detrimental to the regularity and efficiency of the latter.
  • Patent FR 2 422 035 for its part, provides for limiting the disturbance of the parietal film, caused by the dilution air inlet orifices by leaving a free space between the hot shell and the tubular dilution orifice and having a downstream lip at the inner end of the dilution tube in order to restore downstream the film which had been interrupted by the obstacle constituted by the tube.
  • the object of the present invention is to provide a double-walled combustion chamber which allows better coupling of impact, multi-perforation, convection and film cooling and a significant reduction in the flow rates allocated to cooling, this by better control of the formation and optimization of the shape of the parietal cooling films by controlling the respective positioning of the upstream part of each hot shell and the downstream tab of the preceding hot shell, as a function of the expansion of the hot ferrules during operation of the combustion chamber.
  • the invention therefore relates to a double-walled combustion chamber, as defined above and such that the mixing orifices are of the hole-nozzle type comprising a first cylindrical element comprising in combination successively from the outside to the inside from the chamber a flare flared outwards in quarter-round, the flange internally forming an air inlet nozzle and externally comprising a shoulder by which it can rest on the external face of the cold wall without being integral therewith , a first external cylindrical bearing coming to be housed in a circular recess of the cold wall and a second circular bearing on which is concentrically mounted a second ring-shaped element comprising a collar and a tubular bearing arranged inside a recess of the hot wall, against which the tubular bearing is folded back in a fallen edge and such that the ring is welded on the second cylindrical bearing of the pr first element forming a nozzle.
  • the mixing orifices are of the hole-nozzle type comprising a first cylindrical element comprising in combination successively from the outside to the inside from the chamber
  • the first cylindrical bearing surface of the element of the mixing orifice forming hole-nozzle has a length greater than the thickness of the hot wall so that the mixing orifice, integral with the hot wall, or mounted floating on the cold wall of the combustion chamber.
  • each ferrule constituting the hot wall has at its downstream a curved flange allowing its downstream attachment in an annular groove of the cold wall and each of said ferrules is mounted floating upstream relative to the hot wall by means of the only mixing orifices constituting, in addition to their air inlet function, means for radial and axial positioning of the ferrules of the hot wall on the cold wall and means for controlling the expansion clearance of the hot wall.
  • the wall structure can be organized so that the upstream edge of each ferrule of the hot wall cooperates with a tongue downstream of the ferrule located immediately upstream to form the cooling film and that the slit height of the cooling films is controlled during operation by the positioning of said ferrule by means of its mixing orifices and by the inclination of the downstream tongue of the ferrule located immediately upstream, due to the positioning of said upstream ferrule by its own mixing orifices.
  • a low pressure compressor 1 compresses the air drawn at the engine inlet; the flow leaving the low pressure compressor is separated into a primary flow and a secondary flow, the primary flow is compressed again by a high pressure compressor 2 before being mixed with pressurized fuel in an annular combustion chamber 3 such than that of the invention where the mixture is burned to provide combustion energy to the engine.
  • the gases from the chamber 3 drive a turbine 4 which itself drives the compressors 1 and 2. At the outlet of the turbine, the gases are accelerated.
  • the hot flow is then mixed with the cold flow, which at the outlet of the low pressure compressor has flowed into an annular stream formed by the intermediate casing 5 surrounding the hot flow and the external casing 6 of the engine.
  • the gases are then ejected, either dry, or by undergoing a reheating in a post-combustion device 7.
  • FIG. 2 shows in longitudinal section the detail A of FIG. 1.
  • the combustion chamber 3 is an annular double-walled chamber formed by a double internal wall 8, that is to say the one closest to the axis of symmetry of the engine and a double external wall 9 most radially distant from the axis of symmetry of the engine.
  • Each of these double walls 8 and 9 includes an inner wall to the chamber, subjected to combustion gases and called hot wall or hot skin and an outer wall subjected to the flow of primary air cooler than the combustion gases.
  • the cold walls, internal and external, of the chamber are each formed by four ferrules (respectively from upstream to downstream 10, 11, 12, 13; 110, 111, 112, 113) welded together by means of parts massive machined annulars (respectively 14, 15, 16; 114, 115, 116) serving for the attachment of the hot walls and, as regards the piece 114 for the formation of a parietal cooling film.
  • the ferrule 21 has downstream a groove 23 allowing its attachment to a flange 24 of the film 15 of the cold wall while the ferrule 22 has two flanges 25 and 26 which are hung one, 25, on an annular groove of the part machined 16 from the cold wall and the other 26 downstream in a second groove 27 downstream from the internal cold wall.
  • the ferrules 121 and 122 are similarly hung downstream by flanges 123, 125 and 126 in annular grooves of the machined parts 115, 116 and downstream 127 of the external wall.
  • the ferrules 21, 22, 121, 122 have their upstream surfaces mounted floating and are positioned on the cold walls only by the mixing orifices 29, 30 intended for supplying combustion air to the primary zone and the zone of dilution.
  • Each mixing orifice 29 or 30 comprises a first cylindrical element 31 having a central bore 32 flared in quarter round 33 towards the outside and forming the mixing air inlet hole-nozzle.
  • the flange formed by the flared part delimits a shoulder 34 which can be supported on the external face of the cold wall 11 or 12, 111 or 112 while the first external cylindrical bearing 35 penetrates inside two aligned circular recesses 36 , 37 cold and hot skin.
  • a second cylindrical bearing surface 38 of smaller diameter extends the first bearing surface 35.
  • a ring 39 comprising a collar 40 and a tubular bearing surface 41 passing through the orifice 37.
  • the collar 40 is disposed between the hot and cold skins resting against the end of the bearing surface 35, while the end 42 of the bearing surface 41 is folded back on the fallen edge onto the hot skin 21, 22 or 121, 122 once the latter has been assembled.
  • the ring 39 is secured to the nozzle hole 31 by a weld bead deposited between the fallen edge 42 and the seat 38.
  • the thickness of the collar 40 determines the minimum interval between the hot and cold skins while the length of the staff 35 added to the thickness of the collar determines the maximum interval.
  • the cold interval hF between walls is fixed by the thickness of the collar and the hot wall by its expansion during operation tends to deviate from the cold wall and it is then the cumulative height of the bearing surface 35 and the collar 40 which fixes the maximum expansion interval hC when hot.
  • the desired height cold hF can be fixed between the hot and cold skin of the internal wall and the maximum limit of expansion of the hot skin as well as for the external wall. can set the minimum distance between walls to the desired hC value when hot.
  • the assembly of the chamber is carried out as follows:
  • the cooling of the walls of the combustion chamber is achieved by combining a convection flow external to the cold walls, by multi-perforations of the cold walls 10, 11, 12, 13, 110, 111, 112, 113; by convection against the current between cold skins (resp. 11, 12, 13, 111, 112, 113) and hot skins (resp. 21, 22, 121, 122) and by parietal film along the hot ferrules 21 , 22, 121, 122.
  • the machined parts 19, 114 of the primary ferrules have downstream tongues 44, 45 which cooperate with the upstream edge of the ferrules 21 and 121 to form the parietal film for cooling the primary ferrules.
  • the downstream edge of the primary hot shrouds 21, 121 has tongues 46, 47 which cooperate with the upstream edge of the hot dilution shrouds in order to produce the cooling film for said hot dilution shrouds.
  • the radial positioning of the hot ferrules on the cold walls by the mixing orifices 29, 30 allows optimal cooling efficiency by the parietal films to be obtained because it allows the shape of the flow speed cavity to be controlled as well as the slit height of the film, this being able to be better controlled as the thickness of the downstream tabs 44, 45, 46, 47, made in solid parts, can be calculated so that the low expansion of the tongue does not significantly modify the slit height of the film.
  • the fixing of the hot ferrules on the cold walls by the mixing orifices also makes it possible to ensure the circumferential homogeneity of the flow by avoiding the wake phenomena, known in the prior devices and which were due to the expansion limiters.
  • the method of mounting hot skins on cold skins makes it possible to obtain a better compromise between the various cooling modes used while allowing the realization of a double-walled chamber of low weight and technology simple and easy to assemble (or disassemble), which makes its application particularly useful in turbojets for which high performance and high reliability are sought.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Spray-Type Burners (AREA)

Description

La présente invention concerne les chambres de combustion et plus particulièrement les chambres à double paroi, notamment pour turbomachines comprenant au moins une paroi extérieure, dite paroi froide, formée de plusieurs viroles mécanosoudées et destinée à assurer la rigidité mécanique de la chambre de combustion, et comprenant au moins une paroi intérieure, dite paroi chaude destinée à assurer la tenue thermique de la chambre, formée de plusieurs viroles successives assemblées entre elles et sur la paroi froide de façon à laisser libre entre les deux parois un espace de refroidissement permettant un jeu de dilatation de la paroi chaude ; la chambre comprenant également des orifices de mélange traversant les deux parois pour permettre l'introduction d'air de combustion primaire et de dilution à l'intérieur de la chambre.The present invention relates to combustion chambers and more particularly to double-walled chambers, in particular for turbomachines comprising at least one outer wall, known as a cold wall, formed of several mechanically welded ferrules and intended to ensure the mechanical rigidity of the combustion chamber, and comprising at least one inner wall, called the hot wall intended to ensure the thermal resistance of the chamber, formed of several successive ferrules assembled together and on the cold wall so as to leave free between the two walls a cooling space allowing a set of dilation of the hot wall; the chamber also comprising mixing orifices passing through the two walls to allow the introduction of primary combustion and dilution air inside the chamber.

Ce type de chambres de combustion est de plus en plus employé dans les turboréacteurs actuels car leurs taux de compression tendent à s'accroître de jour en jour de même que la température d'entrée de turbine du moteur. En effet, la puissance développé par un moteur est directement liée à la température d'entrée turbine et pour augmenter la puissance, les constructeurs atteignent de nos jours des températures devant turbines qui avoisinent, voire dépassent 1800° K. D'autre part, la consommation spécifique d'un moteur, très élevée à ces températures de travail, décroît lorsque le taux de compression du moteur augmente et pour ne pas obérer ce paramètre, les moteurs actuels voient donc leur taux de compression augmenter. Ces différentes considérations ont amené à créer des chambres de combustion à double paroi de façon à améliorer la protection thermique des parois de la chambre afin d'augmenter la longévité des chambres.This type of combustion chambers is more and more used in current turbojet engines because their compression rates tend to increase day by day as well as the turbine inlet temperature of the engine. Indeed, the power developed by an engine is directly linked to the turbine inlet temperature and to increase the power, manufacturers nowadays reach temperatures in front of turbines which are close to, or even exceed 1800 ° K. On the other hand, the specific consumption of an engine, very high at these working temperatures, decreases when the engine compression rate increases and in order not to obstruct this parameter, current engines therefore see their compression rate increase. These various considerations have led to the creation of double-walled combustion chambers so as to improve the thermal protection of the walls of the chamber in order to increase the longevity of the chambers.

Un exemple en est donné dans le brevet FR 2 340 453 au nom de la demanderesse.An example is given in patent FR 2 340 453 in the name of the applicant.

Diverses techniques de refroidissement sont employées en plus du simple refroidissement par convection externe.Various cooling techniques are used in addition to simple external convection cooling.

Le refroidissement, dit par « film cooling ou film pariétal, utilise l'effet d'écran thermique fourni par des entrées d'air secondaire créant le long de la surface interne de la paroi une couche pariétale évitant le contact direct entre la paroi et les gaz de combustion. Cette couche qui se dilue au fur et à mesure de son parcours d'amont en aval doit être renouvelée au moyen d'entrées d'air successivement distribuées dans la longueur de la chambre.Cooling, known as “film cooling or parietal film, uses the thermal shield effect provided by secondary air inlets creating along the internal surface of the wall a parietal layer avoiding direct contact between the wall and the combustion gases. This layer which dilutes as it travels from upstream to downstream must be renewed by means of air inlets successively distributed in the length of the chamber.

On utilise également le principe du refroidissement par convection entre les deux parois de la chambre soit à co-courant, soit à contre-courant. Dans ce cas le même flux d'air peut servir à refroidir la face externe de la paroi chaude, par convection, puis être utilisé pour former un film pariétal qui refroidira sa face interne. Toutefois, cette disposition exige des débits d'air très importants si l'on désire obtenir des effets de convection notables.The principle of convection cooling between the two walls of the chamber is also used, either co-current or counter-current. In this case, the same air flow can be used to cool the external face of the hot wall, by convection, then be used to form a parietal film which will cool its internal face. However, this arrangement requires very high air flow rates if one wishes to obtain significant convection effects.

Ces types de refroidissement sont néanmoins utilisés mais amènent un certain nombre d'inconvénients. Certains sont liés à la structure même des doubles parois car la paroi chaude doit pouvoir supporter des dilatations notables lors du fonctionnement de la chambre et cela exige de la monter avec jeu par rapport à la paroi froide.These types of cooling are nevertheless used but bring a certain number of drawbacks. Some are linked to the very structure of the double walls because the hot wall must be able to withstand significant expansions during the operation of the chamber and this requires mounting it with play with respect to the cold wall.

Ainsi le brevet US 4 302 941 prévoit une paroi intérieure dont des viroles chaudes étagées sont fixées avec jeu radial par des vis sur la paroi froide tandis que des languettes solidaires de la face externe des viroles chaudes assurent le guidage de l'air de convection et limitent le jeu radial. Toutefois, ces languettes, utiles pour canaliser l'air de convection créent des sillages importants dans le film pariétal formé en sortie de la virole chaude, ce qui perturbe l'efficacité de ce film. D'autre part les orifices d'entrée d'air de dilution, placés directement en sortie du film perturbent également celui-ci.Thus, US Pat. No. 4,302,941 provides an interior wall, of which stepped hot rings are fixed with radial clearance by screws on the cold wall, while tongues integral with the external face of the hot rings ensure the guiding of the convection air and limit the radial clearance. However, these tabs, useful for channeling the convection air, create significant wakes in the parietal film formed at the outlet of the hot shell, which disturbs the effectiveness of this film. On the other hand the dilution air inlet orifices, placed directly at the outlet of the film also disturb the latter.

Le brevet FR 2 023 415 prévoit une chambre de combustion à doubles parois, les viroles internes de la paroi chaude étant étagées et fixées par leur bord amont, tandis que l'aval comprend des patins de limitation du jeu de dilatation de la virole. Un ennui présenté par ce type de chambre qui utilise le principe du refroidissement par convection à co-courant et par film pariétal est de présenter une épaisseur de film qui n'est pas totalement maîtrisée en fonctibn de la dilatation de la paroi chaude. Un autre inconvénient réside dans le fait que, comme dans le dispositif précédent, les patins aval de limitation de jeu introduisent des sillages dans le film pariétal, sillages nuisibles à la régularité et à l'efficacité de celui-ci.Patent FR 2 023 415 provides a combustion chamber with double walls, the internal rings of the hot wall being stepped and fixed by their upstream edge, while the downstream comprises pads for limiting the expansion play of the ring. One annoyance presented by this type of chamber which uses the principle of cooling by co-current convection and by parietal film is to present a film thickness which is not completely controlled in function of the expansion of the hot wall. Another drawback lies in the fact that, as in the previous device, the downstream clearance limitation pads introduce wakes in the parietal film, wakes detrimental to the regularity and efficiency of the latter.

Le brevet FR 2 422 035, quant à lui, prévoit de limiter la perturbation du film pariétal, causée par les orifices d'entrée d'air de dilution en laissant un espace libre entre la virole chaude et l'orifice tubulaire de dilution et en disposant une lèvre aval à l'extrémité intérieure du tube de dilution afin de rétablir en aval le film qui avait été interrompu par l'obstacle constitué par le tube.Patent FR 2 422 035, for its part, provides for limiting the disturbance of the parietal film, caused by the dilution air inlet orifices by leaving a free space between the hot shell and the tubular dilution orifice and having a downstream lip at the inner end of the dilution tube in order to restore downstream the film which had been interrupted by the obstacle constituted by the tube.

La présente invention a pour but de réaliser une chambre de combustion à double parois qui permet un meilleur couplage des refroidissements par impact, multiperforations, convection et par film et une réduction importante des débits alloués au refroidissement, ceci au moyen d'un meilleur contrôle de la formation et de l'optimisation de la forme des films pariétaux de refroidissement par le pilotage du positionnement respectif de la partie amont de chaque virole chaude et de la languette aval de la virole chaude précédente, en fonction de la dilatation des viroles chaudes lors du fonctionnement de la chambre de combustion.The object of the present invention is to provide a double-walled combustion chamber which allows better coupling of impact, multi-perforation, convection and film cooling and a significant reduction in the flow rates allocated to cooling, this by better control of the formation and optimization of the shape of the parietal cooling films by controlling the respective positioning of the upstream part of each hot shell and the downstream tab of the preceding hot shell, as a function of the expansion of the hot ferrules during operation of the combustion chamber.

Elle a également pour but de réaliser une chambre de combustion à double paroi de construction simple permettant de limiter le surplus de masse engendré par une technologie à double paroi, de permettre la démontabilité des viroles de la paroi chaude, de séparer les fonctions de tenue thermique et mécanique, et de simplifier la fixation des viroles de la paroi chaude en permettant leur fixation flottante sur la paroi froide au moyen d'un type particulier d'orifices de mélange.It also aims to produce a double-walled combustion chamber of simple construction making it possible to limit the excess mass generated by a double technology wall, to allow the disassembly of the ferrules from the hot wall, to separate the functions of thermal and mechanical resistance, and to simplify the fixing of the ferrules of the hot wall by allowing their floating fixing on the cold wall by means of a particular type mixing ports.

L'invention a donc pour objet une chambre de combustion à double paroi, telle que définie plus haut et telle que les orifices de mélange sont du type trou-tuyère comportant un premier élément cylindrique comprenant en combinaison successivement de l'extérieur vers l'intérieur de la chambre une collerette évasée vers l'extérieur en quart de rond, la collerette formant intérieurement tuyère d'entrée d'air et comprenant extérieurement un épaulement par lequel elle peut s'appuyer sur la face externe de la paroi froide sans y être solidarisée, une première portée cylindrique extérieure venant se loger dans un évidement circulaire de la paroi froide et une seconde portée circulaire sur laquelle est monté concentriquement un second élément en forme de bague comportant un collet et une portée tubulaire disposée à l'intérieur d'un évidement de la paroi chaude, contre laquelle la portée tubulaire est repliée en bord tombé et telle que la bague est soudée sur la seconde portée cylihdri- que du premier élément formant tuyère.The invention therefore relates to a double-walled combustion chamber, as defined above and such that the mixing orifices are of the hole-nozzle type comprising a first cylindrical element comprising in combination successively from the outside to the inside from the chamber a flare flared outwards in quarter-round, the flange internally forming an air inlet nozzle and externally comprising a shoulder by which it can rest on the external face of the cold wall without being integral therewith , a first external cylindrical bearing coming to be housed in a circular recess of the cold wall and a second circular bearing on which is concentrically mounted a second ring-shaped element comprising a collar and a tubular bearing arranged inside a recess of the hot wall, against which the tubular bearing is folded back in a fallen edge and such that the ring is welded on the second cylindrical bearing of the pr first element forming a nozzle.

Selon une particularité de l'invention, la première portée cylindrique de l'élément de l'orifice de mélange formant trou-tuyère a une longueur supérieure à l'épaisseur de la paroi chaude de telle sorte que l'orifice de mélange, solidaire de la paroi chaude, soit monté flottant sur la paroi froide de la chambre de combustion.According to a feature of the invention, the first cylindrical bearing surface of the element of the mixing orifice forming hole-nozzle has a length greater than the thickness of the hot wall so that the mixing orifice, integral with the hot wall, or mounted floating on the cold wall of the combustion chamber.

Selon une autre particularité de l'invention, chaque virole constituant la paroi chaude comporte à son aval une bride recourbée permettant son accrochage aval dans une rainure annulaire de la paroi froide et chacune des dites viroles est montée flottante en amont par rapport à la paroi chaude au moyen des seuls orifices de mélange constituant, outre leur fonction d'entrée d'air, des moyens de positionnement radial et axial des viroles de la paroi chaude sur la paroi froide et des moyens de contrôle du jeu de dilatation de la paroi chaude.According to another feature of the invention, each ferrule constituting the hot wall has at its downstream a curved flange allowing its downstream attachment in an annular groove of the cold wall and each of said ferrules is mounted floating upstream relative to the hot wall by means of the only mixing orifices constituting, in addition to their air inlet function, means for radial and axial positioning of the ferrules of the hot wall on the cold wall and means for controlling the expansion clearance of the hot wall.

Si l'invention est utilisée dans une chambre de combustion dans laquelle on applique, outre le refroidissement par convection entre les parois, le principe du refroidissement par film pariétal, alors on peut organiser la structure de paroi de telle sorte que le bord amont de chaque virole de la paroi chaude coopère avec une languette aval de la virole située immédiatement en amont pour former le film de refroidissement et que la hauteur de fente des films de refroidissement soit pilotée au cours du fonctionnement par le positionnement de la dite virole au moyen de ses orifices de mélange et par l'inclinaison de la languette aval de la virole située immédiatement en amont, due au positionnement de la dite virole amont par ses propres orifices de mélange.If the invention is used in a combustion chamber in which the principle of wall film cooling is applied, in addition to convection cooling between the walls, then the wall structure can be organized so that the upstream edge of each ferrule of the hot wall cooperates with a tongue downstream of the ferrule located immediately upstream to form the cooling film and that the slit height of the cooling films is controlled during operation by the positioning of said ferrule by means of its mixing orifices and by the inclination of the downstream tongue of the ferrule located immediately upstream, due to the positioning of said upstream ferrule by its own mixing orifices.

Une mode de réalisation de l'invention sera explicitée en regard des planches de dessins annexées parmi lesquelles :

  • - la figure 1 est une coupe schématique d'un turboréacteur incorporant une chambre de combustion selon l'invention ;
  • - la figure 2 montre un mode de réalisation d'une chambre de combustion à double paroi telle que précédemment décrite, en demi-coupe longitudinale selon le détail A de la figure 1 ;
  • - la figure 3 montre en coupe à plus grande échelle le détail d'un orifice de mélange disposé sur la paroi externe de la chambre, c'est-à-dire la paroi la plus éloignée de l'axe longitudinal de symétrie de la chambre, à froid en partie gauche de la figure, et à chaud en partie droite de la figure ;
  • - la figure 4 montre en coupe un orifice de mélange identique au précédent, mais monté sur la paroi interne, c'est-à-dire le plus proche de l'axe, à froid en partie gauche de la figure, et à chaud en partie droite.
An embodiment of the invention will be explained with reference to the accompanying drawing boards, among which:
  • - Figure 1 is a schematic section of a turbojet incorporating a combustion chamber according to the invention;
  • - Figure 2 shows an embodiment of a double-walled combustion chamber as previously described, in longitudinal half-section according to detail A in Figure 1;
  • - Figure 3 shows in section on a larger scale the detail of a mixing orifice disposed on the outer wall of the chamber, that is to say the wall farthest from the longitudinal axis of symmetry of the chamber , cold in the left part of the figure, and hot in the right part of the figure;
  • - Figure 4 shows in section a mixing orifice identical to the previous one, but mounted on the internal wall, that is to say closest to the axis, cold in the left part of the figure, and hot in right side.

En référence à la figure 1 où un moteur double flux à faible taux de dilution a été représenté, on voit que de façon classique un compresseur basse pression 1 comprime l'air aspiré à l'entrée du moteur ; le flux en sortie du compresseur basse pression est séparé en un flux primaire et un flux secondaire, le flux primaire est comprimé à nouveau par un compresseur haute pression 2 avant d'être mélangé à du carburant sous pression dans une chambre de combustion annulaire 3 telle que celle de l'invention où le mélange est brûlé pour apporter une énergie de combustion au moteur. Les gaz issus de la chambre 3 entraînent une turbine 4 qui, elle-même entraîne les compresseurs 1 et 2. En sortie de turbine, les gaz sont accélérés. Le flux chaud est alors mélangé au flux froid, qui en sortie du compresseur basse pression s'est écoulé dans une veine annulaire formée du carter intermédiaire 5 entourant le flux chaud et du carter externe 6 du moteur. Les gaz sont alors éjectés, soit à sec, soit en subissant une rechauffe dans un dispositif de post-combustion 7.Referring to Figure 1 where a double flow motor with low dilution rate has been shown, we see that conventionally a low pressure compressor 1 compresses the air drawn at the engine inlet; the flow leaving the low pressure compressor is separated into a primary flow and a secondary flow, the primary flow is compressed again by a high pressure compressor 2 before being mixed with pressurized fuel in an annular combustion chamber 3 such than that of the invention where the mixture is burned to provide combustion energy to the engine. The gases from the chamber 3 drive a turbine 4 which itself drives the compressors 1 and 2. At the outlet of the turbine, the gases are accelerated. The hot flow is then mixed with the cold flow, which at the outlet of the low pressure compressor has flowed into an annular stream formed by the intermediate casing 5 surrounding the hot flow and the external casing 6 of the engine. The gases are then ejected, either dry, or by undergoing a reheating in a post-combustion device 7.

La figure 2 montre en coupe longitudinale le détail A de la figure 1.FIG. 2 shows in longitudinal section the detail A of FIG. 1.

La chambre de combustion 3 selon l'invention est une chambre annulaire à double parois formée d'une double paroi interne 8, c'est-à-dire la plus proche de l'axe de symétrie du moteur et d'une double paroi externe 9 la plus éloignée radialement de l'axe de symétrie du moteur. Chacune de ces double parois 8 et 9 comprend une paroi intérieure à la chambre, soumise aux gaz de combustion et dite paroi chaude ou peau chaude et une paroi extérieure soumise au flux d'air primaire plus froid que les gaz de combustion.The combustion chamber 3 according to the invention is an annular double-walled chamber formed by a double internal wall 8, that is to say the one closest to the axis of symmetry of the engine and a double external wall 9 most radially distant from the axis of symmetry of the engine. Each of these double walls 8 and 9 includes an inner wall to the chamber, subjected to combustion gases and called hot wall or hot skin and an outer wall subjected to the flow of primary air cooler than the combustion gases.

Pour éviter toute confusion entre les parois intérieures (« chaudes ») à la chambre et la paroi interne de la chambre ainsi qu'entre les parois extérieures (« froides ») à la chambre et la partie externe, on désignera systématiquement dans la suite du texte les parois intérieures par les termes « peaux chaudes ou « parois chaudes et les parois extérieures par « peaux froides ou « parois froides tandis que les expressions « paroi interne et « paroi externe désigneront respectivement la double paroi proche de l'axe de symétrie du moteur et la double paroi la plus éloignée radialement de l'axe de symétrie du moteur.To avoid any confusion between the interior ("hot") walls of the chamber and the internal wall of the chamber as well as between the exterior ("cold") walls of the chamber and the external part, we will systematically designate in the following the text the inner walls with the words "hot skins or" hot walls and the outer walls with "cold skins or" cold walls while the expressions "Inner wall and" outer wall respectively denote the double wall close to the axis of symmetry of the engine and the double wall most radially distant from the axis of symmetry of the engine.

Les parois froides, interne et externe, de la chambre sont formées chacune de quatre viroles (respectivement de l'amont vers l'aval 10, 11, 12, 13 ; 110, 111, 112, 113) soudées entre elles au moyen de pièces annulaires usinées massives (respectivement 14, 15, 16 ; 114, 115, 116) servant à l'accrochage des parois chaudes et, en ce qui concerne la pièce 114 à la formation d'un film pariétal de refroidissement.The cold walls, internal and external, of the chamber are each formed by four ferrules (respectively from upstream to downstream 10, 11, 12, 13; 110, 111, 112, 113) welded together by means of parts massive machined annulars (respectively 14, 15, 16; 114, 115, 116) serving for the attachment of the hot walls and, as regards the piece 114 for the formation of a parietal cooling film.

Les parois chaudes sont constituées :

  • - pour la partie interne d'une virole fixe 17 soudée au fond 18 de la chambre de combustion et comportant une gorge annulaire aval 19 dans laquelle vient se positionner une languette 20 du film 14 de la paroi froide, et de deux viroles 21 et 22 montées flottantes sur la paroi interne froide ;
  • - pour la partie externe de deux viroles 121, 122 montées flottantes sur la paroi externe froide, ainsi qu'on va le voir.
The hot walls are made up of:
  • - For the internal part of a fixed ferrule 17 welded to the bottom 18 of the combustion chamber and comprising a downstream annular groove 19 in which is positioned a tongue 20 of the film 14 of the cold wall, and two ferrules 21 and 22 floating mounted on the cold internal wall;
  • - For the external part of two ferrules 121, 122 mounted floating on the cold external wall, as will be seen.

La virole 21 comporte en aval une rainure 23 permettant son accrochage sur une bride 24 du film 15 de la paroi froide tandis que la virole 22 comporte deux brides 25 et 26 qui sont accrochées l'une, 25, sur une rainure annulaire de la partie usinée 16 de la paroi froide et l'autre 26 en aval dans une seconde rainure 27 de l'aval de la paroi froide interne.The ferrule 21 has downstream a groove 23 allowing its attachment to a flange 24 of the film 15 of the cold wall while the ferrule 22 has two flanges 25 and 26 which are hung one, 25, on an annular groove of the part machined 16 from the cold wall and the other 26 downstream in a second groove 27 downstream from the internal cold wall.

Les viroles 121 et 122 sont accrochées en aval de façon similaire par des brides 123, 125 et 126 dans des rainures annulaires des pièces usinées 115, 116 et de l'aval 127 de la paroi externe.The ferrules 121 and 122 are similarly hung downstream by flanges 123, 125 and 126 in annular grooves of the machined parts 115, 116 and downstream 127 of the external wall.

Les viroles 21, 22, 121, 122 ont leurs portées amont montées flottantes et ne sont positionnées sur les parois froides que par les orifices de mélange 29, 30 destinées à l'alimentation en air de combustion de la zone primaire et de la zone de dilution. Chaque orifice de mélange 29 ou 30 comporte un premier élément cylindrique 31 possédant un alésage central 32 évasé en quart de rond 33 vers l'extérieur et formant le trou-tuyère d'entrée d'air de mélange. La collerette formée par la partie évasée délimite un épaulement 34 qui peut s'appuyer sur la face externe de la paroi froide 11 ou 12, 111 ou 112 tandis que la première portée cylindrique extérieure 35 pénètre à l'intérieur de deux évidements circulaires alignés 36, 37 des peaux froides et chaudes. Une seconde portée cylindrique 38 de moindre diamètre prolonge la première portée 35. Sur cette portée 38 est montée concentriquement une bague 39 comportant un collet 40 et une portée tubulaire 41 traversant l'orifice 37. Le collet 40 est disposé entre les peaux chaudes et froides en appui contre l'extrémité de la portée 35, tandis que l'extrémité 42 de la portée 41 est repliée en bord tombé sur la peau chaude 21, 22 ou 121, 122 une fois celle-ci montée. Ensuite, la bague 39 est solidarisée au trou-tuyère 31 par un cordon de soudure déposé entre le bord tombé 42 et la portée 38.The ferrules 21, 22, 121, 122 have their upstream surfaces mounted floating and are positioned on the cold walls only by the mixing orifices 29, 30 intended for supplying combustion air to the primary zone and the zone of dilution. Each mixing orifice 29 or 30 comprises a first cylindrical element 31 having a central bore 32 flared in quarter round 33 towards the outside and forming the mixing air inlet hole-nozzle. The flange formed by the flared part delimits a shoulder 34 which can be supported on the external face of the cold wall 11 or 12, 111 or 112 while the first external cylindrical bearing 35 penetrates inside two aligned circular recesses 36 , 37 cold and hot skin. A second cylindrical bearing surface 38 of smaller diameter extends the first bearing surface 35. On this bearing surface 38 is concentrically mounted a ring 39 comprising a collar 40 and a tubular bearing surface 41 passing through the orifice 37. The collar 40 is disposed between the hot and cold skins resting against the end of the bearing surface 35, while the end 42 of the bearing surface 41 is folded back on the fallen edge onto the hot skin 21, 22 or 121, 122 once the latter has been assembled. Then, the ring 39 is secured to the nozzle hole 31 by a weld bead deposited between the fallen edge 42 and the seat 38.

L'épaisseur du collet 40 détermine l'intervalle minimal entre les peaux chaudes et froides tandis que la longueur de la portée 35 ajoutée à l'épaisseur du collet en détermine l'intervalle maximal.The thickness of the collar 40 determines the minimum interval between the hot and cold skins while the length of the staff 35 added to the thickness of the collar determines the maximum interval.

Ainsi (figure 3), sur la paroi externe de la chambre, l'échauffement de la paroi chaude lors du fonctionnement de la chambre tend à rapprocher les deux parois qui, à froid étaient séparées d'un intervalle hF déterminé par la hauteur du trou-tuyère 31 jusqu'à la valeur hC (inférieure a hF) égale à l'épaisseur du collet 40.Thus (FIG. 3), on the external wall of the chamber, the heating of the hot wall during operation of the chamber tends to bring the two walls which, when cold, were separated by an interval hF determined by the height of the hole nozzle 31 up to the value hC (less than hF) equal to the thickness of the collar 40.

A l'inverse sur les parois internes, l'intervalle à froid hF entre parois est fixé par l'épaisseur de collet et la paroi chaude par sa dilatation lors du fonctionnement a tendance à s'écarter de la paroi froide et c'est alors la hauteur cumulée de la portée 35 et du collet 40 qui fixe l'intervalle de dilatation maximale hC à chaud.Conversely on the internal walls, the cold interval hF between walls is fixed by the thickness of the collar and the hot wall by its expansion during operation tends to deviate from the cold wall and it is then the cumulative height of the bearing surface 35 and the collar 40 which fixes the maximum expansion interval hC when hot.

De ce fait par le seul calcul des dimensions des trous-tuyères on peut fixer la hauteur souhaitée à froid hF entre peau chaude et froide de la paroi interne et la limite maximale de dilatation de la peau chaude de même que pour la paroi externe, on peut fixer l'intervalle minimal entre parois à la valeur hC désirée à chaud.Therefore, by the sole calculation of the dimensions of the nozzle holes, the desired height cold hF can be fixed between the hot and cold skin of the internal wall and the maximum limit of expansion of the hot skin as well as for the external wall. can set the minimum distance between walls to the desired hC value when hot.

L'assemblage de la chambre s'effectue de la façon suivante :The assembly of the chamber is carried out as follows:

On monte d'abord de part et d'autre de la paroi froide externe 111, 112 les deux éléments 31 et 39 des trous-tuyères 30 puis on accroche la virole 121 par sa bride 123 dans la rainure de la pièce 115 et on positionne la virole 121 au moyen des orifices de mélange 30 dont on vient replier l'extrémité 42 de la bague sur la virole. Enfin on solidarise les éléments 31 et 39. On fait de même avec la virole 122. Les viroles 21 et 22 de la paroi interne sont montées de la même façon sur la peau froide 11, 12, 13 au moyen des orifices de dilution 29 puis l'ensemble de la paroi interne est accroché en 19, 20 sur la virole 17 et fixée par des boulons 43 sur la casquette interne de fond de chambre.We first mount on either side of the external cold wall 111, 112 the two elements 31 and 39 of the nozzle holes 30 then the ferrule 121 is hooked by its flange 123 in the groove of the part 115 and we position the ferrule 121 by means of the mixing orifices 30, the end 42 of the ring of which is just folded over the ferrule. Finally, the elements 31 and 39 are joined together. The same is done with the ferrule 122. The ferrules 21 and 22 of the internal wall are mounted in the same way on the cold skin 11, 12, 13 by means of the dilution orifices 29 then the entire internal wall is hung at 19, 20 on the ferrule 17 and fixed by bolts 43 on the internal cap at the bottom of the chamber.

Le refroidissement des parois de la chambre de combustion est réalisé par combinaison d'un flux de convection externe aux parois froides, par des multiperforations des parois froides 10, 11, 12, 13, 110, 111, 112, 113; par convection à contre-courant entre les peaux froides (resp. 11, 12, 13, 111, 112, 113) et les peaux chaudes (resp. 21, 22, 121, 122) et par film pariétal le long des viroles chaudes 21, 22, 121, 122. Pour ce faire, les parties usinées 19, 114 des viroles primaires comportent des languettes aval 44, 45 qui coopèrent avec le bord amont des viroles 21 et 121 pour former le film pariétal de refroidissement des viroles primaires. De même, le bord aval des viroles chaudes primaires 21, 121 comporte des languettes 46, 47 qui coopèrent avec le bord amont des viroles chaudes de dilution pour réaliser le film de refroidissement des dites viroles chaudes de dilution.The cooling of the walls of the combustion chamber is achieved by combining a convection flow external to the cold walls, by multi-perforations of the cold walls 10, 11, 12, 13, 110, 111, 112, 113; by convection against the current between cold skins (resp. 11, 12, 13, 111, 112, 113) and hot skins (resp. 21, 22, 121, 122) and by parietal film along the hot ferrules 21 , 22, 121, 122. To do this, the machined parts 19, 114 of the primary ferrules have downstream tongues 44, 45 which cooperate with the upstream edge of the ferrules 21 and 121 to form the parietal film for cooling the primary ferrules. Likewise, the downstream edge of the primary hot shrouds 21, 121 has tongues 46, 47 which cooperate with the upstream edge of the hot dilution shrouds in order to produce the cooling film for said hot dilution shrouds.

Le positionnement radial des viroles chaudes sur les parois froides par les orifices de mélange 29, 30 permet d'obtenir une efficacité optimale du refroidissement par les films pariétaux car il permet de contrôler la forme de la cavité de mise en vitesse de l'écoulement ainsi que la hauteur de fente du film, celle-ci pouvant d'autant mieux être contrôlée que l'épaisseur des languettes aval 44, 45, 46, 47, réalisées dans des parties massives, peut être calculée de sorte que la faible dilatation de la languette ne modifie pas sensiblement la hauteur de fente du film.The radial positioning of the hot ferrules on the cold walls by the mixing orifices 29, 30 allows optimal cooling efficiency by the parietal films to be obtained because it allows the shape of the flow speed cavity to be controlled as well as the slit height of the film, this being able to be better controlled as the thickness of the downstream tabs 44, 45, 46, 47, made in solid parts, can be calculated so that the low expansion of the tongue does not significantly modify the slit height of the film.

La fixation des viroles chaudes sur les parois froides par les orifices de mélange permet également d'assurer l'homogénéité circonférentielle de l'écoulement en évitant les phénomènes de sillages, connus dans les dispositifs antérieurs et qui étaient dus aux pontets de limitation de dilatation.The fixing of the hot ferrules on the cold walls by the mixing orifices also makes it possible to ensure the circumferential homogeneity of the flow by avoiding the wake phenomena, known in the prior devices and which were due to the expansion limiters.

Elle permet également de diminuer les sillages amont par une accélération progressive de l'écoulement, obtenue par une loi d'évolution de section dans la partie finale du film.It also makes it possible to reduce the upstream wakes by a progressive acceleration of the flow, obtained by a law of evolution of section in the final part of the film.

Le film pariétal réalisé en amont des viroles aval de dilution 22, 122 n'étant pas suffisant pour garder une efficacité totale sur la longueur, importante, des dites viroles, leur partie convergente est refroidie entre les brides 25, 27 et resp. 125, 126 par impact et par multiperforation de la peau chaude, ainsi que montré à la figure 2.The parietal film produced upstream of the downstream dilution ferrules 22, 122 not being sufficient to keep total efficiency over the long, significant length of said ferrules, their converging part is cooled between the flanges 25, 27 and resp. 125, 126 by impact and by multiperforation of the hot skin, as shown in Figure 2.

Le mode de montage des peaux chaudes sur les peaux froides, proposé par l'invention, permet d'obtenir un meilleur compromis entre les divers modes de refroidissement utilisés tout en permettant la réalisation d'une chambre à doubles parois de faible poids et de technologie simple et de montage (ou de démontage) aisé, qui en rend l'application particulièrement utile dans les turboréacteurs pour lesquels des performances élevées et une grande fiabilité sont recherchées.The method of mounting hot skins on cold skins, proposed by the invention, makes it possible to obtain a better compromise between the various cooling modes used while allowing the realization of a double-walled chamber of low weight and technology simple and easy to assemble (or disassemble), which makes its application particularly useful in turbojets for which high performance and high reliability are sought.

Claims (7)

1. Combustion chamber with a double wall, especially for turbo-engines, comprising at least one outer wall, called a cold wall, formed from several mechanically welded rings and intended for ensuring the mechanical rigidity of the combustion chamber, and comprising at least one inner wall, called a hot wall, intended for ensuring the thermal stability of the chamber and formed from several rings joined to one another and to the outer wall, in such a way as to leave free between the two walls a cooling space allowing an expansion clearance for the hot wall, the chamber having mixing orifices passing through the two walls in order to allow primary combustion air and dilution air to be introduced, characterized in that the mixing orifices (29, 30) are of the nozzlehole type having a first cylindrical element (31) comprising in combination, successively from the outside of the chamber towards the inside, a collar (33) widened outwards in a quarter round, the collar forming on the inside an air inflow nozzle and having on the outside a shoulder (34), by means of which it can bear on the outer face of the cold wall, without being secured to it, a first outer cylindrical bearing surface (35) coming to rest in a circular recess (36) of the cold wall, and a second circular bearing surface (38), on which is mounted concentrically a second element (39) in the form of a hoop, having a flange (40) and a tubular bearing surface (41) arranged inside a recess (37) of the hot wall, against which the tubular bearing surface is bent with a turned-down edge (42), and in that the hoop is welded to the second cylindrical bearing surface of the first element forming a nozzle.
2. Combustion chamber according to Claim 1, characterized in that the first cylindrical bearing surface (35) has a length greater than the thickness of the hot wall, so that the mixing orifice (29, 30) integral with the hot wall is mounted in a floating manner on the cold wall of the combustion chamber.
3. Combustion chamber according to one of Claims 1 or 2, of the annular type, comprising an inner double wall near the axis of symmetry of the chamber and an outer double wall distant from the axis of symmetry of the chamber and having mixing orifices in its inner Wall and its outer wall, characterized in that the thickness of the hoop flange (40) of the orifices (30) in the outer wall is calculated at the height hC desired under hot conditions between the hot wall and cold wall, and in that the thickness of the said flanges (40) of the orifices (29) in the inner wall is calculated at the height desired under cold conditions hF between the hot wall and cold wall.
4. Combustion chamber according to any one of Claims 1 to 3, characterized in that each ring forming the hot wall has, in its downstream direction, a curved lug (23, 26, 123, 126) allowing it to catch downstream in an annular groove of the cold wall, and in that each of the said rings is mounted in a floating manner, upstream, in relation to the hot wall solely by means of the mixing orifices (29, 30) which, in addition to their air inflow function, constitute means for the radial and axial positioning of the rings of the hot wall on the cold wall and means for controlling the expansion clearance for the hot wall.
5. Combustion chamber according to Claim 4, incorporating a cooling by peripheral film, characterized in that the upstream edge of each ring (21, 22, 121, 122) of the hot wall interacts with a downstream tongue (44, 46, 45, 47 respectively) of the ring located immediately upstream, to form the cooling film, and in that the gap height of the cooling films is controlled, during operation, as a result of the positioning of the said ring by means of its mixing orifices and as a result of the inclination of the downstream tongue of the ring located immediately upstream, attributable to the positioning of the said upstream ring by means of its own mixing orifices.
6. Combustion chamber according to any one of Claims 1 to 5, characterized in that it incorporates a cooling of the hot wall by impact via multiple perforations in the cold and hot walls.
7. Combustion chamber according to any one of Claims 1 to 6, characterized in that it incorporates a cooling of the hot wall by counterflow convection between the cold wall and the hot wall.
EP87401235A 1986-06-04 1987-06-03 Gas turbine combustion chamber having mixing orifices which assure the positioning of a hot wall on a cool wall Expired EP0248731B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8608015 1986-06-04
FR8608015A FR2599821B1 (en) 1986-06-04 1986-06-04 COMBUSTION CHAMBER FOR TURBOMACHINES WITH MIXING HOLES PROVIDING THE POSITIONING OF THE HOT WALL ON THE COLD WALL

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EP0248731A1 EP0248731A1 (en) 1987-12-09
EP0248731B1 true EP0248731B1 (en) 1989-01-11

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EP (1) EP0248731B1 (en)
DE (1) DE3760036D1 (en)
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Families Citing this family (41)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2624953B1 (en) * 1987-12-16 1990-04-20 Snecma COMBUSTION CHAMBER FOR TURBOMACHINES HAVING A DOUBLE WALL CONVERGENT
US4887432A (en) * 1988-10-07 1989-12-19 Westinghouse Electric Corp. Gas turbine combustion chamber with air scoops
US5144793A (en) * 1990-12-24 1992-09-08 United Technologies Corporation Integrated connector/airtube for a turbomachine's combustion chamber walls
FR2674317B1 (en) * 1991-03-20 1993-05-28 Snecma COMBUSTION CHAMBER OF A TURBOMACHINE COMPRISING AN ADJUSTMENT OF THE FUEL FLOW.
FR2710968B1 (en) * 1993-10-06 1995-11-03 Snecma Double wall combustion chamber.
US5394688A (en) * 1993-10-27 1995-03-07 Westinghouse Electric Corporation Gas turbine combustor swirl vane arrangement
US5431517A (en) * 1994-01-12 1995-07-11 General Electric Company Apparatus and method for securing a bracket to a fixed member
FR2723177B1 (en) * 1994-07-27 1996-09-06 Snecma COMBUSTION CHAMBER COMPRISING A DOUBLE WALL
DE19547703C2 (en) * 1995-12-20 1999-02-18 Mtu Muenchen Gmbh Combustion chamber, in particular ring combustion chamber, for gas turbine engines
JPH09195799A (en) * 1996-01-17 1997-07-29 Mitsubishi Heavy Ind Ltd Spring seal apparatus for combustor
US6499993B2 (en) * 2000-05-25 2002-12-31 General Electric Company External dilution air tuning for dry low NOX combustors and methods therefor
US6334310B1 (en) * 2000-06-02 2002-01-01 General Electric Company Fracture resistant support structure for a hula seal in a turbine combustor and related method
CN1246638C (en) * 2001-04-27 2006-03-22 西门子公司 Combustion chamber in particulary of gas turbine
EP1312865A1 (en) * 2001-11-15 2003-05-21 Siemens Aktiengesellschaft Gas turbine annular combustion chamber
US8387396B2 (en) 2007-01-09 2013-03-05 General Electric Company Airfoil, sleeve, and method for assembling a combustor assembly
US8281600B2 (en) * 2007-01-09 2012-10-09 General Electric Company Thimble, sleeve, and method for cooling a combustor assembly
US8616004B2 (en) * 2007-11-29 2013-12-31 Honeywell International Inc. Quench jet arrangement for annular rich-quench-lean gas turbine combustors
US8141365B2 (en) * 2009-02-27 2012-03-27 Honeywell International Inc. Plunged hole arrangement for annular rich-quench-lean gas turbine combustors
US8171740B2 (en) * 2009-02-27 2012-05-08 Honeywell International Inc. Annular rich-quench-lean gas turbine combustors with plunged holes
US9010123B2 (en) * 2010-07-26 2015-04-21 Honeywell International Inc. Combustors with quench inserts
US8813501B2 (en) * 2011-01-03 2014-08-26 General Electric Company Combustor assemblies for use in turbine engines and methods of assembling same
US9249679B2 (en) * 2011-03-15 2016-02-02 General Electric Company Impingement sleeve and methods for designing and forming impingement sleeve
JP5821550B2 (en) * 2011-11-10 2015-11-24 株式会社Ihi Combustor liner
US20130298564A1 (en) * 2012-05-14 2013-11-14 General Electric Company Cooling system and method for turbine system
US8695352B2 (en) * 2012-07-12 2014-04-15 Solar Turbines Inc. Baffle assembly for bleed air system of gas turbine engine
DE102012022259A1 (en) * 2012-11-13 2014-05-28 Rolls-Royce Deutschland Ltd & Co Kg Combustor shingle of a gas turbine and process for its production
US20140190171A1 (en) * 2013-01-10 2014-07-10 Honeywell International Inc. Combustors with hybrid walled liners
US20150354819A1 (en) 2013-01-16 2015-12-10 United Technologies Corporation Combustor Cooled Quench Zone Array
US11112115B2 (en) * 2013-08-30 2021-09-07 Raytheon Technologies Corporation Contoured dilution passages for gas turbine engine combustor
US10655855B2 (en) 2013-08-30 2020-05-19 Raytheon Technologies Corporation Gas turbine engine wall assembly with support shell contour regions
WO2015038232A1 (en) * 2013-09-13 2015-03-19 United Technologies Corporation Sealed combustor liner panel for a gas turbine engine
EP3090209B1 (en) 2014-01-03 2019-09-04 United Technologies Corporation A cooled grommet for a combustor wall assembly of a gas turbine
US10533745B2 (en) 2014-02-03 2020-01-14 United Technologies Corporation Film cooling a combustor wall of a turbine engine
US10112557B2 (en) * 2014-04-03 2018-10-30 United Technologies Corporation Thermally compliant grommet assembly
GB201514390D0 (en) 2015-08-13 2015-09-30 Rolls Royce Plc A combustion chamber and a combustion chamber segment
EP3315864B1 (en) * 2016-10-26 2021-07-28 Raytheon Technologies Corporation Cast combustor liner panel with radiused dilution passage grommet for a gas turbine engine combustor
US10697372B2 (en) * 2017-04-05 2020-06-30 General Electric Company Turbine engine conduit interface
GB201720254D0 (en) * 2017-12-05 2018-01-17 Rolls Royce Plc A combustion chamber arrangement
US10816203B2 (en) * 2017-12-11 2020-10-27 General Electric Company Thimble assemblies for introducing a cross-flow into a secondary combustion zone
US11022308B2 (en) 2018-05-31 2021-06-01 Honeywell International Inc. Double wall combustors with strain isolated inserts
US10808930B2 (en) * 2018-06-28 2020-10-20 Raytheon Technologies Corporation Combustor shell attachment

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB845971A (en) * 1958-07-21 1960-08-24 Gen Electric Improvements relating to combustion chambers for gas turbine engines
GB1059199A (en) * 1965-10-20 1967-02-15 Rolls Royce Flame tube
US3496722A (en) * 1968-08-02 1970-02-24 Garrett Corp Combustion chamber flame tube construction
US3899876A (en) * 1968-11-15 1975-08-19 Secr Defence Brit Flame tube for a gas turbine combustion equipment
US3545202A (en) * 1969-04-02 1970-12-08 United Aircraft Corp Wall structure and combustion holes for a gas turbine engine
US4555901A (en) * 1972-12-19 1985-12-03 General Electric Company Combustion chamber construction
US4614082A (en) * 1972-12-19 1986-09-30 General Electric Company Combustion chamber construction
US4480436A (en) * 1972-12-19 1984-11-06 General Electric Company Combustion chamber construction
US4184326A (en) * 1975-12-05 1980-01-22 United Technologies Corporation Louver construction for liner of gas turbine engine combustor
GB2017827B (en) * 1978-04-04 1983-02-02 Gen Electric Combustor liner cooling
US4302941A (en) * 1980-04-02 1981-12-01 United Technologies Corporation Combuster liner construction for gas turbine engine
US4512159A (en) * 1984-04-02 1985-04-23 United Technologies Corporation Clip attachment
FR2567250A1 (en) * 1984-07-06 1986-01-10 Gen Electric Combustion chamber for a gas turbine engine
US4748806A (en) * 1985-07-03 1988-06-07 United Technologies Corporation Attachment means
DE3535443C1 (en) * 1985-10-04 1986-11-20 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Combustion chamber for a gas turbine engine, especially an annular combustion chamber, with at least one air supply bushing

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US4805397A (en) 1989-02-21
FR2599821A1 (en) 1987-12-11
FR2599821B1 (en) 1988-09-02
EP0248731A1 (en) 1987-12-09
DE3760036D1 (en) 1989-02-16

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