EP1496207A1 - Device to passively control the thermal dilatation of a turbomachine housing - Google Patents

Device to passively control the thermal dilatation of a turbomachine housing Download PDF

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Publication number
EP1496207A1
EP1496207A1 EP04291648A EP04291648A EP1496207A1 EP 1496207 A1 EP1496207 A1 EP 1496207A1 EP 04291648 A EP04291648 A EP 04291648A EP 04291648 A EP04291648 A EP 04291648A EP 1496207 A1 EP1496207 A1 EP 1496207A1
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EP
European Patent Office
Prior art keywords
flange
housing
recess
flanges
casing
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
EP04291648A
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German (de)
French (fr)
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EP1496207B1 (en
Inventor
Thomas Chereau
Thierry Jean-Maurice Niclot
Alain Raffy
Patrice Suet
Christophe Yvon Gabriel Tourne
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Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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Publication of EP1496207A1 publication Critical patent/EP1496207A1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion

Definitions

  • the present invention relates to turbojet engines and concerns in particular the high pressure compressor extension housing of turbojet.
  • Turbojets generally comprise at least one low pressure compressor and a high pressure compressor. It is frequent to take gas at a compressor stage so to feed relatively cold fluid from other downstream parts of the turbomachine, for example a turbine distributor, for cooling them or upstream parts, for example for defrosting at the level of low pressure compressor.
  • upstream and downstream will be used to indicate the position of a part in relation to the overall flow of gas during operation of the turbojet engine.
  • the high pressure compressor is located upstream of the chamber of combustion.
  • the compressor comprises a inner casing 2, around which extends a casing 3 said extension.
  • the crankcase extension 3 comprises a downstream flange 4, to secure it with the housing 5 of the combustion chamber 6, and which supports a wall 7 of separation between the two volumes.
  • the downstream flange 4 of the expansion casing 3 is fixedly connected to the upstream flange 8 of the combustion chamber housing 5, by bolts of link 9 located at the level of the distributed flange holes 10 circumferentially to the flange 4.
  • the two flanges 4, 8 of the housing 3 and the combustion chamber 6, enclose an upstream flange 11 of a diffuser cone 12, which is a perforated cone located in the enclosure of the combustion chamber 6.
  • the downstream face 14 of the flange 4 of the casing 3 is flat, pressed against the flange 11 of the diffuser cone 12.
  • the cooling fluid of other elements of the turbojet engine is taken from the seventh stage of the compressor 1, not shown, by orifices provided for this purpose, both on the housing 2 of the compressor and on the expansion casing 3.
  • the space annular 13 located between these two casings 2, 3 is bathed in this fluid.
  • the high speed imposed on the engine causes a high rise the temperature of the air taken from the compressor and thus from the crankcase extension 3, whose skin is quite thin and has low thermal inertia and undergoes significant dilation. It reaches in a short time the temperature about 550 ° C.
  • the flange 4 of this housing 3, more massive and more bathed in the enclosure 15 of the nacelle, remains at this time at a temperature about 200 ° C, especially at its outer periphery.
  • the service life of the expansion case is much longer weak than the goal. It follows during the life of the engine a need in maintenance and a high cost of use related to the removal of the engine outside planned visits.
  • the present invention aims to overcome these disadvantages.
  • the invention relates to a device for driving passively the thermal expansion of the expansion casing of a turbojet engine and relieve stress, said extension housing enveloping the housing high pressure compressor interior of the turbojet, and comprising a flange for fixing to an upstream flange of the housing of the chamber of combustion.
  • This device is characterized by the fact that at least one cavity circumferential is formed between said two flanges in which circulates a stream taken at the inlet of the combustion chamber.
  • the flange of the housing is allowed to expand in depending on the higher temperature of the air taken downstream. Expansion of the piloted flange thus passively accompanies that of the skin of the crankcase and reduces the source of stress between the two parts of the crankcase.
  • the two flanges enclose a holding flange of a diffuser cone, the cavity being formed between one of the crankcase flanges and the flange of the cone diffuser.
  • the cavity is formed by a recess formed in one of said flanges.
  • the recess providing an internal transverse flange and an external transverse support flange on the face of the adjacent flange, the internal axial flange has calibrated perforations forming grooves radial, gas inlet, and the flange includes calibrated perforations forming outlet channels of the gas stream.
  • the channels comprise an inlet orifice located in the recess and an outlet opening into the space ring located between the compressor housing and the expansion housing.
  • the cavity is formed of several recesses arranged circumferentially in sectors, each recess communicating with a radial groove and a channel.
  • the throat radial is located at a transverse end of the recess and the channel is located at the other transverse end of the recess.
  • the turbojet engine comprises a high pressure compressor 21 and a combustion chamber 26.
  • the compressor comprises a casing 22, wrapped by an expansion casing 23.
  • the compressor housing 22 and the extension casing 23 are connected by a wall 27 with a Y-shaped section, the two branches of the Y being directed towards the downstream part of the turbojet, one supporting the compressor housing 22 and the other being supported by an inlet flange 24 of the extension casing 23.
  • the combustion chamber 26 comprises a housing 25, which comprises an upstream flange 28.
  • the upstream flange of the combustion chamber 28 and the downstream flange of the extension casing 24 are connected by connecting bolts 29, through, in particular, holes 30 in the flange of the extension casing 24.
  • the two flanges grip, in a fixed manner, an upstream flange 31 of a cone diffuser 32.
  • This diffuser cone 32 is a perforated cone extending into the chamber of the combustion chamber 26, and whose role is to guide and to diffuse gas flows.
  • the flange of the extension casing 24 of the invention comprises, on its downstream face 34, a circumferential recess 40, providing a flange internal transverse 41 and an external transverse flange 42 bearing on the face upstream of the upstream flange of the diffuser cone 31.
  • the internal transverse flange 41 of the flange of the extension casing 24 has calibrated perforations forming radial grooves 43. Furthermore, the flange of the extension casing 24 comprises calibrated perforations forming channels 44, the inlet port is in the recess 40 and the outlet orifice in the annular space 33 located between the housing of the compressor 22 and the extension housing 23.
  • Each groove 43 and each channel 44 is drilled, at the recess 40, to the right of a flange hole 30, in order to limit overstressing on board.
  • the annular space 33 located between the compressor housing 22 and the extension housing 23 is bathed in gas taken downstream of the last compressor stage 21, here on the seventh floor, which supplies fluid from a relative point of view, other downstream parts of the turbomachine, for example example a turbine distributor, for cooling, or in hot fluid, from a relative point of view, parts upstream, for example for the defrosting at the low pressure compressor. Ports are provided for this purpose, both on the compressor housing 22 and on the housing extension 23.
  • the rear flange of the extension casing 24 is circumferentially divided into sectors 50, 51, 52, for example, in the case of the invention of eight.
  • Each sector comprises a recess 40, a groove 43 at one end transverse of the recess 40 and a channel 44 at the other end of the recess 40.
  • the sectors are separated by radial walls 53, 54.
  • the enclosure of the combustion chamber is bathed in a gas at the temperature of 650 ° C and at the pressure of 40 bar, while the annular space 33 located between the compressor housing 22 and the extension housing 23 is bathed in a gas at a temperature of 550 ° C and a pressure of 25 bar.
  • the housing flange extension 24 is bathed in the enclosure 35 of the nacelle of the turbojet engine.
  • the cavity 45 formed by the recess 40 between the downstream face 34 of the housing flange extension 24, its transverse inner rim 41, its transverse flange 42 and the upstream face of the front flange of the diffuser cone 31, is flow of gas from the enclosure of the chamber of combustion 26.
  • This gas flow maintained by the pressure difference will heat the flange 24, because of its high temperature compared to that of this last.
  • the invention thus makes it possible to assist the expansion of the flange 24 and to reduce the thermal gradient between it and the expansion case 23.
  • the invention has been described in the context of the flange between the housing extension and the chamber cover but it applies to any flange subject to significant thermal gradients.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The device has two clamps, where one clamp (24) is fixed to the upstream of the other clamp. A circumferential cavity is arranged between the two clamps, and a flow of gas prevailing at an inlet of a combustion chamber circulates in the cavity. The cavity is formed by a recess (40) arranged in the clamp (24), and the clamps enclose a maintenance clamp of a diffuser cone.

Description

La présente invention se rapporte aux turboréacteurs et concerne en particulier le carter d'extension de compresseur haute pression de turboréacteur.The present invention relates to turbojet engines and concerns in particular the high pressure compressor extension housing of turbojet.

Les turboréacteurs comprennent généralement au moins un compresseur basse pression et un compresseur haute pression. Il est fréquent de prélever du gaz au niveau d'un étage de compresseur afin d'alimenter en fluide relativement froid d'autres parties aval de la turbomachine, par exemple un distributeur de turbine, pour les refroidir ou des parties situées en amont, par exemple pour le dégivrage au niveau du compresseur basse pression.Turbojets generally comprise at least one low pressure compressor and a high pressure compressor. It is frequent to take gas at a compressor stage so to feed relatively cold fluid from other downstream parts of the turbomachine, for example a turbine distributor, for cooling them or upstream parts, for example for defrosting at the level of low pressure compressor.

Dans toute la description, les termes "amont" et "aval" seront utilisés pour signifier la position d'une pièce par rapport au flux global des gaz pendant le fonctionnement du turboréacteur.Throughout the description, the terms "upstream" and "downstream" will be used to indicate the position of a part in relation to the overall flow of gas during operation of the turbojet engine.

Le compresseur haute pression est situé en amont de la chambre de combustion. En référence aux figures 1 et 2, le compresseur comprend un carter intérieur 2, autour duquel s'étend un carter 3 dit d'extension. Le carter d'extension 3 comprend une bride aval 4, permettant de le solidariser avec le carter 5 de la chambre de combustion 6, et qui supporte une paroi 7 de séparation entre les deux volumes.The high pressure compressor is located upstream of the chamber of combustion. With reference to FIGS. 1 and 2, the compressor comprises a inner casing 2, around which extends a casing 3 said extension. The crankcase extension 3 comprises a downstream flange 4, to secure it with the housing 5 of the combustion chamber 6, and which supports a wall 7 of separation between the two volumes.

La bride aval 4 du carter d'extension 3 est liée de manière fixe à la bride amont 8 du carter de la chambre de combustion 5, par des boulons de liaison 9 se situant au niveau des trous 10 de bride répartis circonférentiellement à la bride 4. Les deux brides 4, 8, du carter d'extension 3 et de la chambre de combustion 6, enserrent une bride amont 11 d'un cône diffuseur 12, qui est un cône ajouré se situant dans l'enceinte de la chambre de combustion 6. La face aval 14 de la bride 4 du carter d'extension 3 est plane, plaquée contre la bride 11 du cône diffuseur 12.The downstream flange 4 of the expansion casing 3 is fixedly connected to the upstream flange 8 of the combustion chamber housing 5, by bolts of link 9 located at the level of the distributed flange holes 10 circumferentially to the flange 4. The two flanges 4, 8 of the housing 3 and the combustion chamber 6, enclose an upstream flange 11 of a diffuser cone 12, which is a perforated cone located in the enclosure of the combustion chamber 6. The downstream face 14 of the flange 4 of the casing 3 is flat, pressed against the flange 11 of the diffuser cone 12.

Dans le cas considéré, le fluide de refroidissement d'autres éléments du turboréacteur est prélevé au niveau du septième étage du compresseur 1, non représenté, par des orifices ménagés à cet effet, à la fois sur le carter 2 du compresseur et sur le carter d'extension 3. Il en résulte que l'espace annulaire 13 situé entre ces deux carters 2, 3 est baigné dans ce fluide. In the case considered, the cooling fluid of other elements of the turbojet engine is taken from the seventh stage of the compressor 1, not shown, by orifices provided for this purpose, both on the housing 2 of the compressor and on the expansion casing 3. As a result, the space annular 13 located between these two casings 2, 3 is bathed in this fluid.

Lors de la phase de décollage d'un avion équipé d'un tel turboréacteur, le haut régime imposé au moteur entraíne une forte élévation de la température de l'air prélevé au compresseur et donc du carter d'extension 3, dont la peau étant assez mince est à faible inertie thermique et subit une dilation importante. Elle atteint en peu de temps la température d'environ 550°C. La bride 4 de ce carter 3, plus massive et de plus baignée dans l'enceinte 15 de la nacelle, reste à ce moment à une température d'environ 200°C, au niveau notamment de sa périphérie extérieure.During the take-off phase of an aircraft equipped with such turbojet, the high speed imposed on the engine causes a high rise the temperature of the air taken from the compressor and thus from the crankcase extension 3, whose skin is quite thin and has low thermal inertia and undergoes significant dilation. It reaches in a short time the temperature about 550 ° C. The flange 4 of this housing 3, more massive and more bathed in the enclosure 15 of the nacelle, remains at this time at a temperature about 200 ° C, especially at its outer periphery.

Il en résulte un très fort gradient thermique entre le carter d'extension 3 et sa bride 4. Ce gradient a pour effet de provoquer la flexion de la bride 4 et de fortes contraintes tangentielles au niveau du haut des trous de bride 10.This results in a very strong thermal gradient between the housing 3 and its flange 4. This gradient has the effect of causing flexion of the flange 4 and strong tangential stresses at the top of the flange holes 10.

Du fait des contraintes importantes résultant du gradient thermique susmentionné, la durée de vie du carter d'extension est beaucoup plus faible que l'objectif. Il s'ensuit pendant la vie du moteur un besoin en maintenance et un coût d'utilisation élevé lié à la dépose du moteur en dehors des visites prévues.Due to the important constraints resulting from the thermal gradient mentioned above, the service life of the expansion case is much longer weak than the goal. It follows during the life of the engine a need in maintenance and a high cost of use related to the removal of the engine outside planned visits.

La présente invention vise à pallier ces inconvénients.The present invention aims to overcome these disadvantages.

A cet effet, l'invention concerne un dispositif pour piloter passivement la dilation thermique du carter d'extension d'un turboréacteur et en soulager les contraintes, ledit carter d'extension enveloppant le carter intérieur de compresseur haute pression du turboréacteur, et comportant une bride de fixation à une bride amont du carter de la chambre de combustion. Ce dispositif est caractérisé par le fait qu'au moins une cavité circonférentielle est ménagée entre les dites deux brides dans laquelle circule un flux prélevé en entrée de la chambre de combustion.For this purpose, the invention relates to a device for driving passively the thermal expansion of the expansion casing of a turbojet engine and relieve stress, said extension housing enveloping the housing high pressure compressor interior of the turbojet, and comprising a flange for fixing to an upstream flange of the housing of the chamber of combustion. This device is characterized by the fact that at least one cavity circumferential is formed between said two flanges in which circulates a stream taken at the inlet of the combustion chamber.

Grâce à l'invention, on permet à la bride du carter de se dilater en fonction de la température plus élevée de l'air prélevé en aval. La dilatation de la bride pilotée ainsi passivement accompagne donc celle de la peau du carter et réduit les source de contraintes entre les deux parties du carter.Thanks to the invention, the flange of the housing is allowed to expand in depending on the higher temperature of the air taken downstream. Expansion of the piloted flange thus passively accompanies that of the skin of the crankcase and reduces the source of stress between the two parts of the crankcase.

On connaít un dispositif de dilatation assistée d'une bride de carter, par le document US 6, 352, 404, qui décrit l'interface entre deux brides longitudinales de fixation de deux demi-portions de carter de compresseur ou de turbine, dans lesquelles est ménagée une cavité de pilotage passif de la dilatation des brides, en vue d'éviter l'ovalisation du carter ; le problème résolu est donc différent de celui de l'invention. Le dispositif de l'invention diffère en outre de celui de ce document, tout d'abord, du fait qu'il ne s'agit pas d'une bride longitudinale du carter du compresseur mais d'une bride transversale de son carter d'extension, ensuite, parce que l'air de pilotage est prélevé en entrée de la chambre de combustion et non dans la veine de gaz du compresseur.There is known a device for assisted expansion of a housing flange, US 6, 352, 404, which describes the interface between two flanges longitudinal fixing of two half-portions of compressor housing or turbine, in which is formed a cavity of passive piloting of the expansion of the flanges, in order to avoid the ovalization of the housing; the problem solved is different from that of the invention. The device of the invention also differs from that in this document, first of all because it is not not a longitudinal flange of the compressor housing but a flange transverse of its extension casing, then, because the pilot air is taken at the entrance of the combustion chamber and not in the vein of compressor gas.

En particulier les deux brides enserrent une bride de maintien d'un cône diffuseur, la cavité étant ménagée entre l'une des brides de carter et la bride du cône diffuseur.In particular the two flanges enclose a holding flange of a diffuser cone, the cavity being formed between one of the crankcase flanges and the flange of the cone diffuser.

Selon un mode de réalisation préféré, la cavité est formée par un évidement ménagé dans l'une des dites brides. On peut ainsi aménager la circulation du fluide de réchauffement, grâce à des perforations calibrées ménagées dans la bride et à la différence de pression entre l'amont et l'aval de la bride.According to a preferred embodiment, the cavity is formed by a recess formed in one of said flanges. We can thus develop the circulation of the heating fluid, thanks to calibrated perforations in the flange and at the pressure difference between upstream and downstream of the bridle.

Notamment, l'évidement ménageant un rebord transversal interne et un rebord transversal externe d'appui sur la face de la bride adjacente, le rebord axial interne comporte des perforations calibrées formant des gorges radiales, d'entrée de gaz, et la bride comprend des perforations calibrées formant des canaux de sortie du flux de gaz.In particular, the recess providing an internal transverse flange and an external transverse support flange on the face of the adjacent flange, the internal axial flange has calibrated perforations forming grooves radial, gas inlet, and the flange includes calibrated perforations forming outlet channels of the gas stream.

Plus particulièrement, les canaux comprennent un orifice d'entrée se situant dans l'évidement et un orifice de sortie débouchant dans l'espace annulaire situé entre le carter du compresseur et le carter d'extension.More particularly, the channels comprise an inlet orifice located in the recess and an outlet opening into the space ring located between the compressor housing and the expansion housing.

Selon un mode particulier de réalisation, la cavité est formée de plusieurs évidements disposés circonférentiellement en secteurs, chaque évidement communiquant avec une gorge radiale et un canal. La gorge radiale est située à une extrémité transversale de l'évidement et le canal est situé à l'autre extrémité transversale de l'évidement.According to a particular embodiment, the cavity is formed of several recesses arranged circumferentially in sectors, each recess communicating with a radial groove and a channel. The throat radial is located at a transverse end of the recess and the channel is located at the other transverse end of the recess.

L'invention sera mieux comprise à l'aide de la description suivante de la forme de réalisation préférée du dispositif de l'invention, en rapport avec le dessin annexé, sur lequel :

  • la figure 1 représente une vue de côté en coupe d'une bride de l'art antérieur ;
  • la figure 2 représente une vue en coupe et en perspective de la bride de la figure 1 ;
  • la figure 3 représente une vue de côté en coupe de la forme de réalisation préférée d'une bride de l'invention ;
  • la figure 4 représente une vue en coupe et en perspective de la bride de la figure 3, et
  • la figure 5 représente une vue en perspective de la bride de l'invention.
The invention will be better understood with the aid of the following description of the preferred embodiment of the device of the invention, with reference to the appended drawing, in which:
  • Figure 1 shows a side view in section of a flange of the prior art;
  • Figure 2 shows a sectional and perspective view of the flange of Figure 1;
  • Figure 3 shows a sectional side view of the preferred embodiment of a flange of the invention;
  • FIG. 4 represents a sectional and perspective view of the flange of FIG. 3, and
  • Figure 5 shows a perspective view of the flange of the invention.

En référence aux figures 3 et 4, le turboréacteur comprend un compresseur haute pression 21 et une chambre de combustion 26. Le compresseur comprend un carter 22, enveloppé par un carter d'extension 23. Dans la partie aval du compresseur 21, le carter du compresseur 22 et le carter d'extension 23 sont reliés par une paroi 27 à section en forme de Y, les deux branches du Y étant dirigées vers la partie aval du turboréacteur, l'une supportant le carter du compresseur 22 et l'autre étant supportée par une bride avale 24 du carter d'extension 23.With reference to FIGS. 3 and 4, the turbojet engine comprises a high pressure compressor 21 and a combustion chamber 26. The compressor comprises a casing 22, wrapped by an expansion casing 23. In the downstream part of the compressor 21, the compressor housing 22 and the extension casing 23 are connected by a wall 27 with a Y-shaped section, the two branches of the Y being directed towards the downstream part of the turbojet, one supporting the compressor housing 22 and the other being supported by an inlet flange 24 of the extension casing 23.

La chambre de combustion 26 comporte un carter 25, qui comprend une bride amont 28. La bride amont de la chambre de combustion 28 et la bride aval du carter d'extension 24 sont liées par des boulons de liaison 29, à travers notamment des trous 30 de la bride du carter d'extension 24. Les deux brides enserrent, de manière fixe, une bride amont 31 d'un cône diffuseur 32. Ce cône diffuseur 32 est un cône ajouré s'étendant dans l'enceinte de la chambre de combustion 26, et dont le rôle est de guider et diffuser les flux de gaz.The combustion chamber 26 comprises a housing 25, which comprises an upstream flange 28. The upstream flange of the combustion chamber 28 and the downstream flange of the extension casing 24 are connected by connecting bolts 29, through, in particular, holes 30 in the flange of the extension casing 24. The two flanges grip, in a fixed manner, an upstream flange 31 of a cone diffuser 32. This diffuser cone 32 is a perforated cone extending into the chamber of the combustion chamber 26, and whose role is to guide and to diffuse gas flows.

La bride du carter d'extension 24 de l'invention comporte, sur sa face aval 34, un évidement circonférentiel 40, ménageant un rebord transversal interne 41 et un rebord transversal externe 42 d'appui sur la face amont de la bride amont du cône diffuseur 31.The flange of the extension casing 24 of the invention comprises, on its downstream face 34, a circumferential recess 40, providing a flange internal transverse 41 and an external transverse flange 42 bearing on the face upstream of the upstream flange of the diffuser cone 31.

Le rebord transversal interne 41 de la bride du carter d'extension 24 comporte des perforations calibrées formant des gorges radiales 43. En outre, la bride du carter d'extension 24 comprend des perforations calibrées formant des canaux 44, dont l'orifice d'entrée se situe dans l'évidement 40 et l'orifice de sortie dans l'espace annulaire 33 situé entre le carter du compresseur 22 et le carter d'extension 23. Chaque gorge 43 et chaque canal 44 est percé, au niveau de l'évidement 40, au droit d'un trou de bride 30, afin de limiter les surcontraintes à son bord. The internal transverse flange 41 of the flange of the extension casing 24 has calibrated perforations forming radial grooves 43. furthermore, the flange of the extension casing 24 comprises calibrated perforations forming channels 44, the inlet port is in the recess 40 and the outlet orifice in the annular space 33 located between the housing of the compressor 22 and the extension housing 23. Each groove 43 and each channel 44 is drilled, at the recess 40, to the right of a flange hole 30, in order to limit overstressing on board.

L'espace annulaire 33 situé entre le carter du compresseur 22 et le carter d'extension 23 est baigné dans du gaz prélevé en aval du dernier étage de compresseur 21, ici au septième étage, qui alimente en fluide froid, d'un point de vue relatif, d'autres parties aval de la turbomachine, par exemple un distributeur de turbine, pour les refroidir, ou en fluide chaud, d'un point de vue relatif, des parties situées en amont, par exemple pour le dégivrage au niveau du compresseur basse pression. Des orifices sont ménagés à cet effet, à la fois sur le carter du compresseur 22 et sur le carter d'extension 23.The annular space 33 located between the compressor housing 22 and the extension housing 23 is bathed in gas taken downstream of the last compressor stage 21, here on the seventh floor, which supplies fluid from a relative point of view, other downstream parts of the turbomachine, for example example a turbine distributor, for cooling, or in hot fluid, from a relative point of view, parts upstream, for example for the defrosting at the low pressure compressor. Ports are provided for this purpose, both on the compressor housing 22 and on the housing extension 23.

Plus précisément, et en référence à la figure 5, la bride arrière du carter d'extension 24 est divisée circonférentiellement en secteurs 50, 51, 52, par exemple, dans le cas de l'invention au nombre de huit. Chaque secteur comprend un évidement 40, une gorge 43 à une extrémité transversale de l'évidement 40 et un canal 44 à l'autre extrémité de l'évidement 40. Les secteurs sont séparés par des parois radiales 53, 54.More specifically, and with reference to FIG. 5, the rear flange of the extension casing 24 is circumferentially divided into sectors 50, 51, 52, for example, in the case of the invention of eight. Each sector comprises a recess 40, a groove 43 at one end transverse of the recess 40 and a channel 44 at the other end of the recess 40. The sectors are separated by radial walls 53, 54.

L'intérêt de la bride 24 de l'invention va maintenant être expliqué plus en détail. A la fin du décollage de l'avion, par exemple, l'enceinte de la chambre de combustion est baignée dans un gaz à la température de 650°C et à la pression de 40 bar, tandis que l'espace annulaire 33 situé entre le carter du compresseur 22 et le carter d'extension 23 est baigné dans un gaz à la température de 550°C et à la pression de 25 bar. La bride du carter d'extension 24 est baignée dans l'enceinte 35 de la nacelle du turboréacteur.The interest of the flange 24 of the invention will now be explained more in detail. At the end of the takeoff of the aircraft, for example, the enclosure of the combustion chamber is bathed in a gas at the temperature of 650 ° C and at the pressure of 40 bar, while the annular space 33 located between the compressor housing 22 and the extension housing 23 is bathed in a gas at a temperature of 550 ° C and a pressure of 25 bar. The housing flange extension 24 is bathed in the enclosure 35 of the nacelle of the turbojet engine.

En raison de la différence de pression existant entre l'enceinte de la chambre de compression 26 et l'espace annulaire 33 situé entre le carter du compresseur 22 et le carter d'extension 23, le gaz de l'enceinte de la chambre de combustion 26 passe, au niveau de chaque secteur 50, 51, 52 de la bride du carter d'extension 24, dans les gorges radiales 43 pour ressortir, par les canaux 44, dans l'espace annulaire 33.Due to the pressure difference between the enclosure of the compression chamber 26 and the annular space 33 located between the housing of the compressor 22 and the extension housing 23, the gas of the enclosure of the combustion chamber 26 passes, at each sector 50, 51, 52 of the flange of the extension casing 24, in the radial grooves 43 for leave, through the channels 44, in the annular space 33.

Il en résulte, au niveau de chaque secteur 50, 51, 52, que la cavité 45, ménagée par l'évidement 40 entre la face avale 34 de la bride du carter d'extension 24, son rebord transversal interne 41, son rebord transversal externe 42 et la face amont de la bride avant du cône diffuseur 31, est parcourue par un flux de gaz provenant de l'enceinte de la chambre de combustion 26. As a result, at the level of each sector 50, 51, 52, the cavity 45, formed by the recess 40 between the downstream face 34 of the housing flange extension 24, its transverse inner rim 41, its transverse flange 42 and the upstream face of the front flange of the diffuser cone 31, is flow of gas from the enclosure of the chamber of combustion 26.

Ce flux de gaz entretenu par la différence de pression va chauffer la bride 24, du fait de sa température élevée par rapport à celle de cette dernière. L'invention permet donc d'assister la dilatation de la bride 24 et de diminuer le gradient thermique existant entre elle et le carter d'extension 23.This gas flow maintained by the pressure difference will heat the flange 24, because of its high temperature compared to that of this last. The invention thus makes it possible to assist the expansion of the flange 24 and to reduce the thermal gradient between it and the expansion case 23.

La durée de vie de la bride 24 en raison de l'atténuation des contraintes est ainsi prolongée, ce qui évite éventuellement son remplacement durant la durée de vie du turboréacteur. Après sa circulation dans la cavité 45 de la bride 24, le gaz est réinjecté dans l'espace annulaire 33, ce qui n'affecte que très peu le fonctionnement du turboréacteur, du moins pas de façon significative.The life of the flange 24 due to the attenuation of constraints is thus prolonged, which eventually avoids replacement during the life of the turbojet engine. After its circulation in the cavity 45 of the flange 24, the gas is reinjected into the annular space 33, which affects very little the operation of the turbojet engine, the less not significantly.

L'invention a été décrite dans le cadre de la bride entre le carter d'extension et le carter de chambre mais elle s'applique à toute bride soumise à des gradients thermiques importants.The invention has been described in the context of the flange between the housing extension and the chamber cover but it applies to any flange subject to significant thermal gradients.

Claims (10)

Dispositif pour piloter passivement la dilation thermique du carter d'extension (23) d'un turboréacteur et en soulager les contraintes, ledit carter d'extension (23) enveloppant le carter intérieur (2) de compresseur haute pression (1) du turboréacteur, et comportant une bride (24) de fixation à une bride amont (28) du carter (25) de la chambre de combustion (26), caractérisé par le fait qu'au moins une cavité (45) circonférentielle est ménagée entre les dites deux brides (24 et 28) dans laquelle circule du gaz prélevé en entrée de la chambre de combustion (26).Device for passively controlling the thermal expansion of the extension casing (23) of a turbojet engine and relieving its stresses, said expansion casing (23) enveloping the inner casing (2) of the high-pressure compressor (1) of the turbojet engine, and comprising a flange (24) for fixing to an upstream flange (28) of the casing (25) of the combustion chamber (26), characterized in that at least one circumferential cavity (45) is provided between said two flanges (24 and 28) in which circulates gas taken at the inlet of the combustion chamber (26). Dispositif selon la revendication 1 dans lequel les deux brides enserrent une bride (31) de maintien d'un cône diffuseur (32), la cavité étant ménagée entre une (24) des brides de carter et la bride du cône diffuseur.Device according to claim 1 wherein the two flanges enclose a flange (31) for holding a diffuser cone (32), the cavity being formed between one (24) of the housing flanges and the flange of the diffuser cone. Dispositif selon l'une des revendications 1 ou 2 dans lequel la cavité est formée par un évidement (40) ménagé dans une (24) des dites brides.Device according to one of claims 1 or 2 wherein the cavity is formed by a recess (40) formed in one (24) of said flanges. Dispositif selon la revendication 1, 2 ou 3 dans lequel la circulation du flux de gaz se fait grâce à des perforations calibrées (43, 44) ménagées dans une bride.Device according to claim 1, 2 or 3 wherein the circulation the gas flow is done through calibrated perforations (43, 44) arranged in a flange. Dispositif selon la revendication 4, dans lequel, l'évidement (40) ménageant un rebord transversal interne (41) et un rebord transversal externe (42) d'appui sur la face de la bride adjacente, le rebord axial interne (41) comporte des perforations calibrées formant des gorges radiales (43), d'entrée de gaz, et la bride (24) comprend des perforations calibrées formant des canaux (44), de sortie du flux de gaz.Device according to claim 4, wherein the recess (40) providing an inner transverse flange (41) and a transverse flange external (42) support on the face of the flange adjacent, the axial flange internal (41) has calibrated perforations forming grooves radially (43), gas inlet, and the flange (24) comprises calibrated perforations forming channels (44), output of the flow of gas. Dispositif selon la revendication 5, dans lequel les canaux (44) comprennent un orifice d'entrée se situant dans l'évidement (40) et un orifice de sortie débouchant dans l'espace annulaire (33) situé entre le carter du compresseur (22) et le carter d'extension (23).Device according to claim 5, wherein the channels (44) include an inlet port located in the recess (40) and a outlet opening into the annular space (33) between the compressor housing (22) and the expansion housing (23). Dispositif selon l'une des revendications 3 à 6, dont la cavité est formée de plusieurs évidements disposés circonférentiellement en secteurs (50, 51, 52), chaque évidement (40) communiquant avec une gorge radiale (43) et un canal (44).Device according to one of Claims 3 to 6, the cavity of which is formed of several recesses arranged circumferentially in sectors (50, 51, 52), each recess (40) communicating with a radial groove (43) and a channel (44). Dispositif selon l'une des revendications 1 à 7, dont les brides comportent des trous de bride (30) disposés circonférentiellement, destinés à permettre le passage de liaisons boulons (29) pour la fixation de la bride (24) avec la bride amont (31) du cône diffuseur (32) et la bride amont (28) du carter (25) de la chambre de combustion (26).Device according to one of claims 1 to 7, whose flanges have flange holes (30) arranged circumferentially, intended to allow the passage of bolt connections (29) for the fixing the flange (24) with the upstream flange (31) of the diffuser cone (32) and the upstream flange (28) of the housing (25) of the chamber combustion (26). Dispositif selon la revendication 8, dans lequel les gorges radiales (43) sont percées au droit d'un trou de bride (30).Device according to claim 8, in which the radial grooves (43) are drilled in line with a flange hole (30). Dispositif selon la revendication 9, dans lequel les canaux (44) sont percés au droit d'un trou de bride (30).Device according to claim 9, wherein the channels (44) are pierced at the right of a flange hole (30).
EP04291648A 2003-07-11 2004-06-30 Device to passively control the thermal dilatation of a turbomachine housing Expired - Lifetime EP1496207B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0308584A FR2857409B1 (en) 2003-07-11 2003-07-11 DEVICE FOR PASSIVELY PILOTING THE THERMAL EXPANSION OF THE EXPANSION BOX OF A TURBOREACTOR
FR0308584 2003-07-11

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EP1496207A1 true EP1496207A1 (en) 2005-01-12
EP1496207B1 EP1496207B1 (en) 2006-12-20

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US (1) US7185499B2 (en)
EP (1) EP1496207B1 (en)
JP (1) JP4174039B2 (en)
CA (1) CA2472939C (en)
DE (1) DE602004003749T2 (en)
FR (1) FR2857409B1 (en)
RU (1) RU2343298C2 (en)

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FR2857409A1 (en) 2005-01-14
JP4174039B2 (en) 2008-10-29
RU2343298C2 (en) 2009-01-10
CA2472939A1 (en) 2005-01-11
EP1496207B1 (en) 2006-12-20
CA2472939C (en) 2012-03-27
US7185499B2 (en) 2007-03-06
DE602004003749T2 (en) 2007-10-11
RU2004121114A (en) 2006-01-10
FR2857409B1 (en) 2006-07-28
US20050204746A1 (en) 2005-09-22
JP2005030402A (en) 2005-02-03
DE602004003749D1 (en) 2007-02-01

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