EP0337852A1 - Thermaly regulated exhaust channel for a turbo machine - Google Patents

Thermaly regulated exhaust channel for a turbo machine Download PDF

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Publication number
EP0337852A1
EP0337852A1 EP89400929A EP89400929A EP0337852A1 EP 0337852 A1 EP0337852 A1 EP 0337852A1 EP 89400929 A EP89400929 A EP 89400929A EP 89400929 A EP89400929 A EP 89400929A EP 0337852 A1 EP0337852 A1 EP 0337852A1
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EP
European Patent Office
Prior art keywords
hub
tube
block
turbomachine
internal
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Granted
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EP89400929A
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German (de)
French (fr)
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EP0337852B1 (en
Inventor
Michel Serge Guimier
Patrick Kapala
Philippe Paris
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Safran Aircraft Engines SAS
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Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • 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
    • F01D25/30—Exhaust heads, chambers, or the like

Definitions

  • the present invention relates to a turbomachine exhaust casing, in one-piece structure, provided with a thermal regulation device.
  • turbomachinery It is common in the construction of turbomachinery to provide at the outlet of the turbine an exhaust casing with a monobloc structure comprising connecting arms between an external annular part and an internal annular part, between which is formed a gas circulation channel hot.
  • a monobloc structure comprising connecting arms between an external annular part and an internal annular part, between which is formed a gas circulation channel hot.
  • this is particularly the case for an aeronautical propulsion assembly comprising a gas generator followed by associated free turbines, in which the continuity of the aerodynamic flow stream of hot gases is ensured by an assembly of the aforementioned type which is called in this case inter-turbine structure.
  • This monobloc assembly consisting for example of a casting part, is formed in this case of four coxial ferrules connected by a plurality of profiled arms: an external ferrule which delimits the motor externally at this level, two intermediate ferrules which delimit externally and internally the gas stream and an internal boxed ferrule forming the hub or the centering support of the entire structure.
  • an external ferrule which delimits the motor externally at this level
  • two intermediate ferrules which delimit externally and internally the gas stream
  • an internal boxed ferrule forming the hub or the centering support of the entire structure.
  • such a turbomachine exhaust casing is characterized in that it is associated with a thermal regulation device consisting of a gas sampling tube, a first fixed end of which is in communication with said stream of hot gases and a second end of which enters the box formed by the hub so that the gas flow rate is regulated by the variation of the clearance j between the second tube end and the cooperating hub wall, which results from the relative radial displacements between said tube and hub coming from their thermal state.
  • said first tube end is fixed to said internal intermediate ferrule and cooperates with a sampling hole formed on said ferrule, said tube passes through a sliding guide passage constituted by an orifice formed on the radially part outer of said hub and said second tube end has a flange which faces a block placed in the radially internal part of said hub.
  • a complementary means can be associated with said block, making it possible to adjust the radial position of the block and consequently to fix the clearance j o existing when cold between said flange and the cooperating face of said block.
  • FIG. 1 represents a portion of a known type of propulsion assembly comprising a gas generator associated with free turbines.
  • a mono-block inter-turbine structure 1 is disposed between a low-pressure turbine 2 of a gas generator of which only the downstream two-stage portion of blades 2a and 2b has been shown in the drawing and said free turbines of which only the inlet channel 3 has been shown in the drawing.
  • Said inter-turbine structure or exhaust casing 1 comprises an external ferrule 4, externally delimiting the engine at this level, an external intermediate ferrule 5, an internal intermediate ferrule 6, connected to the previous one by a plurality of profiled arms 7, circumferentially and regularly distributed, an internal ferrule, boxed, delimiting an annular cavity in box 8a and forming a hub 8.
  • the intermediate ferrules 5 and 6 delimit a channel 9 for circulation of hot gases between the turbine outlet of the gas generator and the entry into free turbines.
  • said inter-turbine structure 1 is associated in accordance with the invention with a thermal regulation device, ensuring in particular the heating of said hub 8 during the transient phases of operation of the machine, particularly takeoff.
  • This device comprises a tube 10, a first end 10a of which is fixed to the internal intermediate ferrule 6, in line with a sampling hole 11 which places it in communication with the stream of hot gases circulating in the channel 9.
  • the tube 10 passes through an orifice 12 formed on the radially external annular part 8b of the hub 8 and constituting a sliding guide passage.
  • the radially internal part of the tube 10 is thus housed in the annular cavity 8a of the hub 8 and the second end of the tube 10 has a flange 10b.
  • a clearance j o is thus determined when cold between the facing faces of said flange 10b and of said block 13.
  • the radially external part 8b of the hub 8 has a hole 15 for evacuating the gases having circulated in the annular cavity 8a of the hub 8.
  • T2 increases very quickly compared to T1. It follows from formula (1) that the clearance j takes a maximum value also corresponding to a maximum value of the flow of hot gases sampled for heating the hub 8. Very quickly and taking into account that the efficiency reheating has been calculated so as to ensure this result, the temperature T1 approaches the temperature T2, the difference between T2 and T1 is reduced to a minimum value as well as the variation of the play which takes the stabilized value j s .
  • the sample taken delays the appearance of an inverted gradient such that the temperature T1 becomes higher than the temperature T2, which corresponds to a clearance less than the initial value j o .
  • the invention which has just been described thus makes it possible to obtain the desired results, by means of a regulation of the flow rate of gases sampled by variation of the clearance j, corresponding to the section of passage of the warming gases and obtained by the combination differential thermal expansion between the ferrules of the inter-turbine structure 1 and the sampling tube 10.
  • a maximum flow rate of hot gas is obtained in the transient operating phase of the machine when the hub needs to be heated and , on the contrary, only a minimum flow is ensured under steady conditions, thus avoiding damaging the performance of the machine.

Abstract

A turbomachine exhaust housing of one-piece structure comprises an outer shell (4), two intermediate shells (5, 6) delimiting the hot-gas passage and an inner shell (8) forming a caisson hub (8a). A tube (10) extracting the gases from said passage at a first end (10a) penetrates into the caisson (8a) at a second end (10b) which regulates the gas flow as a result of the variations in the play j between said second end (10b) and the co-operating wall (8c and 13) of the hub as a function of the relative radial displacements between the tube (10) and the hub (8) according to the thermal states of the assembly as a whole. <IMAGE>

Description

La présente invention concerne un carter d'échappement de turbomachine, à structure monobloc, muni d'un dispositif de régulation thermique.The present invention relates to a turbomachine exhaust casing, in one-piece structure, provided with a thermal regulation device.

Il est fréquent dans la construction des turbomachines de prévoir à la sortie de la turbine un carter d'échappement à structure monobloc comportant des bras de liaison entre une partie annulaire externe et une partie annulaire interne, entre lesquelles est ménagé un canal de circulation des gaz chauds. Parmi les applications visées par l'invention, c'est notamment le cas pour un ensemble aéronautique de propulsion comportant un générateur de gaz suivi de turbines libres associées, dans lequel la continuité de la veine aérodynamique de circulation des gaz chauds est assurée par un ensemble du type précité qui est dénommé dans ce cas structure inter-turbine. Cet ensemble monobloc, constitué par exemple d'une pièce de fonderie coulée, est formé dans ce cas de quatre viroles coxiales reliées par une pluralité de bras profilés : une virole externe qui délimite extérieurement le moteur à ce niveau, deux viroles intermédiaires qui délimitent extérieurement et intérieurement la veine de gaz et une virole interne caissonnée formant le moyeu ou le support de centrage de l'ensemble de la structure. En cours de fonctionnement de la turbomachine, des gradients thermiques importants apparaissent dans cette structure inter-turbine entre les parties intermédiaires qui sont en contact direct avec le flux des gaz chauds sortant des turbines du générateur de gaz et notamment le moyeu interne qui reste relativement froid. Ces gradients thermiques, à l'origine de contraintes mécaniques élevées et notamment sous forme de chocs thermiques lors des phases transitoires de fonctionnement de la turbomachine, telles que le décollage dans les applications aéronau­tiques, sont préjudiciables à une tenue correcte des pièces en service. Des tentatives de solution, prévoyant par exemple, d'assurer un réchauffage du moyeu par prélè­vement d'air de veine circulant dans les bras de liaison se sont révélées insuffisantes. L'invention vise à résoudre ces problèmes, tout en évitant de pénaliser le cycle thermodynamique pendant des phases de fonctionnement stabilisé de la turbomachine, notamment en régime de croisière dans les applications aéronautiques et dans ce but, en limitant les périodes de prélèvement aux phases de fonctionnement transitoire durant lesquelles un réchauffage du moyeu interne de la structure monobloc est utile. Ces résultats sont obtenus au moyen d'un dispositif de régulation thermique que l'invention prévoît d'adjoindre à la structure monobloc qui est connue en soi. Par suite, un tel carter d'échappement de turbomachine est caractérisé en ce qu'il est associé à un dispositif de régulation thermique constitué d'un tube de prélèvement de gaz dont une première extrémité fixe est en communication avec ladite veine de gaz chauds et dont une seconde extrémité pénètre dans le caisson formé par le moyeu de manière à ce que le débit de gaz prélevé soit régulé par la variation du jeu j entre la seconde extrémité de tube et la paroi coopérante de moyeu,qui résulte des déplacements radiaux relatifs entre lesdits tube et moyeu provenant de leur état thermique.It is common in the construction of turbomachinery to provide at the outlet of the turbine an exhaust casing with a monobloc structure comprising connecting arms between an external annular part and an internal annular part, between which is formed a gas circulation channel hot. Among the applications targeted by the invention, this is particularly the case for an aeronautical propulsion assembly comprising a gas generator followed by associated free turbines, in which the continuity of the aerodynamic flow stream of hot gases is ensured by an assembly of the aforementioned type which is called in this case inter-turbine structure. This monobloc assembly, consisting for example of a casting part, is formed in this case of four coxial ferrules connected by a plurality of profiled arms: an external ferrule which delimits the motor externally at this level, two intermediate ferrules which delimit externally and internally the gas stream and an internal boxed ferrule forming the hub or the centering support of the entire structure. During the operation of the turbomachine, significant thermal gradients appear in this inter-turbine structure between the intermediate parts which are in direct contact with the flow of hot gases leaving the turbines of the gas generator and in particular the internal hub which remains relatively cold. . These thermal gradients, at the origin of high mechanical stresses and in particular in the form of thermal shocks during the transient phases of operation of the turbomachine, such as takeoff in aeronautical applications, are detrimental to the correct maintenance of the parts in service. Attempts at a solution, for example providing for heating the hub by taking air from the vein circulating in the link arms have proved insufficient. The invention aims to solve these problems, while avoiding penalizing the thermodynamic cycle during stabilized operating phases of the turbomachine, in particular at cruising speed in aeronautical applications and for this purpose, by limiting the sampling periods to the phases of transient operation during which reheating of the internal hub of the one-piece structure is useful. These results are obtained by means of a thermal regulation device which the invention plans to add to the one-piece structure which is known per se. Consequently, such a turbomachine exhaust casing is characterized in that it is associated with a thermal regulation device consisting of a gas sampling tube, a first fixed end of which is in communication with said stream of hot gases and a second end of which enters the box formed by the hub so that the gas flow rate is regulated by the variation of the clearance j between the second tube end and the cooperating hub wall, which results from the relative radial displacements between said tube and hub coming from their thermal state.

Selon des dispositions avantageuses de l'invention, ladite première extrémité de tube est fixée sur ladite virole intermédiaire interne et coopère avec un trou de prélèvement ménagé sur ladite virole, ledit tube traverse un passage de guidage coulissant constitué par un orifice ménagé sur la partie radialement externe dudit moyeu et ladite seconde extrémité de tube comporte une collerette qui fait face à un bloc placé dans la partie radialement interne dudit moyeu.According to advantageous arrangements of the invention, said first tube end is fixed to said internal intermediate ferrule and cooperates with a sampling hole formed on said ferrule, said tube passes through a sliding guide passage constituted by an orifice formed on the radially part outer of said hub and said second tube end has a flange which faces a block placed in the radially internal part of said hub.

En outre, un moyen complémentaire peut être associé audit bloc, permettant de régler la position radiale du bloc et en conséquence de fixer le jeu jo existant à froid entre ladite collerette et la face coopérante dudit bloc.In addition, a complementary means can be associated with said block, making it possible to adjust the radial position of the block and consequently to fix the clearance j o existing when cold between said flange and the cooperating face of said block.

D'autres caractéristiques et avantages de l'invention seront mieux compris à la lecture de la description qui va suivre d'un mode de réalisation, en référence aux dessins annexés sur lesquels :

  • - la figure 1 représente une vue schématique, en coupe longitudinale par un plan passant par l'axe de rotation d'une turbomachine, d'un carter d'échappement de turbomachine ou structure inter-turbine associé à un dispositif de régulation thermique conforme à l'invention ;
  • - la figure 2 représente dans une vue schématique un détail agrandi de la figure 1 montrant ledit dispositif de régulation thermique ;
  • - la figure 3 représente dans une vue schématique en coupe transversale le moyeu de carter d'échappement associé au dispositif de régulation thermique.
Other characteristics and advantages of the invention will be better understood on reading the following description of an embodiment, with reference to the appended drawings in which:
  • - Figure 1 shows a schematic view, in longitudinal section through a plane passing through the axis of rotation of a turbomachine, of a turbomachine exhaust casing or inter-turbine structure associated with a thermal regulation device in accordance with the invention;
  • - Figure 2 shows in a schematic view an enlarged detail of Figure 1 showing said thermal regulation device;
  • - Figure 3 shows in a schematic cross-sectional view the exhaust casing hub associated with the thermal regulation device.

La figure 1 représente une portion d'un ensemble de propulsion de type connu comportant un générateur de gaz associé à des turbines libres. Une structure monobloc inter-turbine 1 est disposée entre une turbine basse-­pression 2 de générateur de gaz dont seule la partie aval à deux étages d'aubes 2a et 2b a été représentée au dessin et lesdites turbines libres dont seul le canal d'entrée 3 a été représenté au dessin. Ladite structure inter-turbine ou carter d'échappement 1 comporte une virole externe 4, délimitant extérieurement le moteur à ce niveau, une virole intermédiaire externe 5, une virole intermédiaire interne 6, reliée à la précédente par une pluralité de bras profilés 7, circonférentiellement et régulièrement répartis, une virole interne, caissonnée, délimitant une cavité annulaire en caisson 8a et formant un moyeu 8. Les viroles intermédiaires 5 et 6 délimitent un canal 9 de circulation des gaz chauds entre la sortie de turbine du générateur de gaz et l'entrée dans les turbines libres.FIG. 1 represents a portion of a known type of propulsion assembly comprising a gas generator associated with free turbines. A mono-block inter-turbine structure 1 is disposed between a low-pressure turbine 2 of a gas generator of which only the downstream two-stage portion of blades 2a and 2b has been shown in the drawing and said free turbines of which only the inlet channel 3 has been shown in the drawing. Said inter-turbine structure or exhaust casing 1 comprises an external ferrule 4, externally delimiting the engine at this level, an external intermediate ferrule 5, an internal intermediate ferrule 6, connected to the previous one by a plurality of profiled arms 7, circumferentially and regularly distributed, an internal ferrule, boxed, delimiting an annular cavity in box 8a and forming a hub 8. The intermediate ferrules 5 and 6 delimit a channel 9 for circulation of hot gases between the turbine outlet of the gas generator and the entry into free turbines.

Comme représenté plus en détails sur les figures 2 et 3, ladite structure inter-turbine 1 est associée conformément à l'invention à un dispositif de régulation thermique, assurant notamment le réchauffage dudit moyeu 8 lors des phases transitoires de fonctionnement de la machine, particulièrement à un régime de décollage.As shown in more detail in FIGS. 2 and 3, said inter-turbine structure 1 is associated in accordance with the invention with a thermal regulation device, ensuring in particular the heating of said hub 8 during the transient phases of operation of the machine, particularly takeoff.

Ce dispositif comporte un tube 10 dont une première extrémité 10a est fixée sur la virole intermédiaire interne 6, au droit d'un trou de prélèvement 11 qui le met en communication avec la veine des gaz chauds circulant dans le canal 9. Le tube 10 traverse un orifice 12 ménagé sur la partie annulaire radialement externe 8b du moyeu 8 et constituant un passage de guidage coulissant. La partie radialement interne du tube 10 est ainsi logée dans la cavité annulaire 8a du moyeu 8 et la seconde extrémité du tube 10 comporte une collerette 10b. Sur la partie annulaire radialement interne 8c du moyeu 8, est placé, au droit de ladite seconde extrémité 10b du tube 10 un bloc 13 dont la position radiale peut être réglée grâce à un moyen de commande 14 de tout type connu, par exemple à vis. Un jeu jo est ainsi déterminé à froid entre les faces en regard de ladite collerette 10b et dudit bloc 13.This device comprises a tube 10, a first end 10a of which is fixed to the internal intermediate ferrule 6, in line with a sampling hole 11 which places it in communication with the stream of hot gases circulating in the channel 9. The tube 10 passes through an orifice 12 formed on the radially external annular part 8b of the hub 8 and constituting a sliding guide passage. The radially internal part of the tube 10 is thus housed in the annular cavity 8a of the hub 8 and the second end of the tube 10 has a flange 10b. On the radially internal annular part 8c of the hub 8, is placed, in line with said second end 10b of the tube 10, a block 13 whose radial position can be adjusted by means of a control means 14 of any known type, for example with screws . A clearance j o is thus determined when cold between the facing faces of said flange 10b and of said block 13.

Du côté diamétralement opposé à l'orifice 12 de passage du tube 10 la partie radialement externe 8b du moyeu 8 comporte un trou d'évacuation 15 des gaz ayant circulé dans la cavité annulaire 8a du moyeu 8.On the side diametrically opposite to the orifice 12 for passage of the tube 10, the radially external part 8b of the hub 8 has a hole 15 for evacuating the gases having circulated in the annular cavity 8a of the hub 8.

Le fonctionnement du dispositif de régulation thermique associé à la structure inter-turbine 1 qui vient d'être décrit peut être brièvement expliqué de la manière suivante. Si on désigne par R₁ le rayon de la seconde extrémité 10b du tube 10, par R₂ le rayon de la première extrémité 10a du tube 10, par T₁ la température, à un instant donné du fonctionnement de la machine, du moyeu 8, par T₂ la température, qui est pratiquement à tout instant identique, de la virole intermédiaire interne 6 et du tube 10, par a, le coefficient de dilatation thermique, également supposé identique de ladite virole intermédiaire interne 6 et dudit tube 10, la variation du jeu j entre les faces en regard de la collerette 10b du tube 10 et du bloc 13 ainsi obtenue est donnée par :
Δj = a R₂ T₂ - a ( R₂-R₁) T₂ - a R₁T₁
soit, on obtient :
Δj = a R₁ ( T₂-T₁ )      (1)The operation of the thermal regulation device associated with the inter-turbine structure 1 which has just been described can be briefly explained in the following manner. If we designate by R₁ the radius of the second end 10b of the tube 10, by R₂ the radius of the first end 10a of the tube 10, by T₁ the temperature, at a given instant of operation of the machine, of the hub 8, by T₂ the temperature, which is practically identical at all times, of the internal intermediate shell 6 and of the tube 10, by a, the coefficient of thermal expansion, also assumed to be identical, of said internal intermediate shell 6 and of said tube 10, the variation of the clearance j between the opposite faces of the collar 10b of the tube 10 and of the block 13 thus obtained is given by:
Δj = a R₂ T₂ - a (R₂-R₁) T₂ - a R₁T₁
either, we obtain:
Δj = a R₁ (T₂-T₁) (1)

On détermine à l'arrêt, à froid, un jeu jo légèrement inférieur au jeu js qui est prévu dans des conditions de fonctionnement stabilisées.It is determined when stopped, when cold, a clearance j o slightly lower than the clearance j s which is provided under stabilized operating conditions.

Au démarrage, T₂ augmente très vite par rapport à T₁. Il résulte de la formule (1) que le jeu j prend une valeur maximale correspondant également à une valeur maximale du débit de gaz chauds prélevés pour le réchauffage du moyeu 8. Très rapidement et compte-tenu du fait que l'efficacité du réchauffage a été calculée de manière à assurer ce résultat, la température T₁ se rapproche de la température T₂, l'écart entre T₂ et T₁ se réduit à une valeur minimale ainsi que la variation du jeu qui prend la valeur stabilisée js.At start-up, T₂ increases very quickly compared to T₁. It follows from formula (1) that the clearance j takes a maximum value also corresponding to a maximum value of the flow of hot gases sampled for heating the hub 8. Very quickly and taking into account that the efficiency reheating has been calculated so as to ensure this result, the temperature T₁ approaches the temperature T₂, the difference between T₂ and T₁ is reduced to a minimum value as well as the variation of the play which takes the stabilized value j s .

En décélération, le prélèvement effectué retarde l'apparition d'un gradient inversé tel que la température T₁ devienne supérieure à la température T₂, ce qui correspond à un jeu inférieur à la valeur initiale jo.When decelerating, the sample taken delays the appearance of an inverted gradient such that the temperature T₁ becomes higher than the temperature T₂, which corresponds to a clearance less than the initial value j o .

L'invention qui vient d'être décrite permet ainsi d'obtenir les résultats recherchés, au moyen d'une régu­lation du débit de gaz prélevés par variation du jeu j, correspondant à la section de passage des gaz de réchauffe et obtenue par la combinaison des dilatations différentielles d'origine thermique entre les viroles de la structure inter-turbine 1 et le tube de prélèvement 10. Un débit maximal de gaz chaud est obtenu en phase transitoire de fonctionnement de la machine lorsque le moyeu a besoin d'être réchauffé et, au contraire, seul un débit minimal est assuré en régime stabilisé, évitant ainsi de porter préjudice aux performances de la machine.The invention which has just been described thus makes it possible to obtain the desired results, by means of a regulation of the flow rate of gases sampled by variation of the clearance j, corresponding to the section of passage of the warming gases and obtained by the combination differential thermal expansion between the ferrules of the inter-turbine structure 1 and the sampling tube 10. A maximum flow rate of hot gas is obtained in the transient operating phase of the machine when the hub needs to be heated and , on the contrary, only a minimum flow is ensured under steady conditions, thus avoiding damaging the performance of the machine.

Claims (3)

1. Carter d'échappement de turbomachine à structure monobloc comportant notamment une virole externe (4), deux viroles intermédiaires (5, 6), reliées par des bras pro­filés (7) et délimitant la veine de circulation des gaz chauds et une virole interne (8), caissonnée formant moyeu caractérisé en ce qu'il est associé à un dispositif de régulation thermique constitué d'un tube (10) de prélè­vement de gaz dont une première extrémité fixe (10a) est en communication avec ladite veine de gaz chauds et dont une seconde extrémité (10b) pénètre dans le caisson (8a) formé par le moyeu (8) de manière à ce que le débit de gaz prélevé soit régulé par la variation du jeu j entre la seconde extrémité (10b) de tube et la paroi coopérante (8c et 13) de moyeu qui résulte des déplacements radiaux relatifs entre lesdits tube (10) et moyeu (8) provenant de leur état thermique.1. Exhaust casing of a turbomachine with a monobloc structure comprising in particular an external shroud (4), two intermediate shrouds (5, 6), connected by profiled arms (7) and delimiting the hot gas circulation stream and an internal shroud (8), boxed forming a hub, characterized in that it is associated with a thermal regulation device consisting of a tube (10) for taking gas, a first fixed end (10a) of which is in communication with said stream of hot gases. and a second end (10b) of which enters the box (8a) formed by the hub (8) so that the flow rate of gas withdrawn is regulated by the variation of the clearance j between the second end (10b) of tube and the cooperating wall (8c and 13) of the hub which results from the relative radial displacements between said tube (10) and hub (8) coming from their thermal state. 2. Carter d'échappement de turbomachine selon la reven­dication 1 dans lequel ladite première extrémité (10a) de tube est fixée sur ladite virole intermédiaire interne (11) et coopère avec un trou de prélèvement (11) ménagé sur ladite virole, ledit tube (10) traverse un passage de guidage coulissant constitué par un orifice (12) ménagé sur la partie radialement externe (8b) dudit moyeu (8) et ladite seconde extrémité de tube comporte une collerette (10b) qui fait face à un bloc (13) placé dans la partie radialement interne (8c) dudit moyeu (8).2. Turbomachine exhaust casing according to claim 1, in which said first tube end (10a) is fixed to said internal intermediate ferrule (11) and cooperates with a sampling hole (11) formed on said ferrule, said tube ( 10) passes through a sliding guide passage constituted by an orifice (12) formed on the radially external part (8b) of said hub (8) and said second tube end comprises a flange (10b) which faces a block (13) placed in the radially internal part (8c) of said hub (8). 3. Carter d'échappement de turbomachine selon la reven­dication 2 dans lequel un moyen complémentaire (14) est associé audit bloc (13), permettant de régler la position radiale du bloc (13) et en conséquence de fixer le jeu jo existant à froid entre ladite collerette (10b) et la face coopérante dudit bloc (13).3. Turbomachine exhaust casing according to claim 2 in which an additional means (14) is associated with said block (13), making it possible to adjust the radial position of the block (13) and consequently to fix the clearance j o existing at cold between said flange (10b) and the cooperating face of said block (13).
EP89400929A 1988-04-13 1989-04-05 Thermaly regulated exhaust channel for a turbo machine Expired - Lifetime EP0337852B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8804860A FR2630159B1 (en) 1988-04-13 1988-04-13 TURBOMACHINE EXHAUST CASING WITH THERMAL REGULATION DEVICE
FR8804860 1988-04-13

Publications (2)

Publication Number Publication Date
EP0337852A1 true EP0337852A1 (en) 1989-10-18
EP0337852B1 EP0337852B1 (en) 1991-09-04

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP89400929A Expired - Lifetime EP0337852B1 (en) 1988-04-13 1989-04-05 Thermaly regulated exhaust channel for a turbo machine

Country Status (4)

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US (1) US4900220A (en)
EP (1) EP0337852B1 (en)
DE (1) DE68900234D1 (en)
FR (1) FR2630159B1 (en)

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EP0509802A1 (en) * 1991-04-16 1992-10-21 General Electric Company Tip clearance control apparatus

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US5316437A (en) * 1993-02-19 1994-05-31 General Electric Company Gas turbine engine structural frame assembly having a thermally actuated valve for modulating a flow of hot gases through the frame hub
US7797946B2 (en) * 2006-12-06 2010-09-21 United Technologies Corporation Double U design for mid-turbine frame struts
EP2861847B1 (en) 2012-06-15 2020-03-25 United Technologies Corporation High durability turbine exhaust case
FR3011035B1 (en) * 2013-09-25 2015-10-09 Snecma EXHAUST CASE COMPRISING A FLUID EVACUATION DEVICE, AND TURBOMACHINE

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FR1360000A (en) * 1963-04-22 1964-04-30 Cem Comp Electro Mec Temperature conditioning device for turbo-machine shafts
CH512664A (en) * 1969-08-04 1971-09-15 Gen Electric Method for cooling the housing of a turbo machine for compressible media and device for carrying out the method
US3704075A (en) * 1970-12-14 1972-11-28 Caterpillar Tractor Co Combined turbine nozzle and bearing frame
US4321007A (en) * 1979-12-21 1982-03-23 United Technologies Corporation Outer case cooling for a turbine intermediate case

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FR1360000A (en) * 1963-04-22 1964-04-30 Cem Comp Electro Mec Temperature conditioning device for turbo-machine shafts
CH512664A (en) * 1969-08-04 1971-09-15 Gen Electric Method for cooling the housing of a turbo machine for compressible media and device for carrying out the method
US3704075A (en) * 1970-12-14 1972-11-28 Caterpillar Tractor Co Combined turbine nozzle and bearing frame
US4321007A (en) * 1979-12-21 1982-03-23 United Technologies Corporation Outer case cooling for a turbine intermediate case

Cited By (1)

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Publication number Priority date Publication date Assignee Title
EP0509802A1 (en) * 1991-04-16 1992-10-21 General Electric Company Tip clearance control apparatus

Also Published As

Publication number Publication date
EP0337852B1 (en) 1991-09-04
FR2630159B1 (en) 1990-07-20
US4900220A (en) 1990-02-13
DE68900234D1 (en) 1991-10-10
FR2630159A1 (en) 1989-10-20

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