EP1580403A1 - Annular sheet metal seal for sealing the space between an inner and an outer turbomachine casing - Google Patents

Annular sheet metal seal for sealing the space between an inner and an outer turbomachine casing Download PDF

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Publication number
EP1580403A1
EP1580403A1 EP05290664A EP05290664A EP1580403A1 EP 1580403 A1 EP1580403 A1 EP 1580403A1 EP 05290664 A EP05290664 A EP 05290664A EP 05290664 A EP05290664 A EP 05290664A EP 1580403 A1 EP1580403 A1 EP 1580403A1
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EP
European Patent Office
Prior art keywords
seal
turbojet
axial wall
section according
wall
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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.)
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EP05290664A
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German (de)
French (fr)
Inventor
Claude Lejars
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Safran Aircraft Engines SAS
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SNECMA SAS
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Publication date
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Publication of EP1580403A1 publication Critical patent/EP1580403A1/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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements

Definitions

  • the invention relates to the sealing between two enclosures of a turbojet engine delimited by crankcases and subjected to pressure different.
  • turbojet section having an outer casing having a radially extending surface inward, an inner casing having a substantially axial wall which extends towards said surface and a seal disposed between said wall and said surface and intended to ensure the seal between the regions to high and low pressures located on either side of said seal.
  • a turbojet engine has an annular channel in which circulates a hot working fluid whose temperature and pressure vary depending on the power demanded from the motor. These variations of temperature causes dilation of the casings surrounding the channel, and certain parts, particularly at the turbine level, subject to highest temperatures require cooling with air fresh under high pressure. Cooling is carried out by a air sampling at a stage of the high pressure compressor. This cooling air circulates in enclosures arranged between a outer casing and an inner casing of the compressor and turbines.
  • FIG. 1 Another technique used in a high compressor pressure, shown in Figure 1, is to position between two radial surfaces provided, facing each other, one on the outer casing and the other on the inner casing, an Omega-type annular seal present in the form of a bellows maintained in compression between said two surfaces.
  • this Omega seal is held radially between two annular complementary axial walls, formed one on the housing inside and the other on the outer casing, of which at least one extends the radial surface of the other housing and may be subject to constraints axial under certain operating conditions of the turbojet engine. This requires additional machining operations to achieve these complementary axial walls which, under certain conditions, prevent free expansion of the inner casing relative to the outer casing.
  • the invention has the primary purpose of sealing between two casings of a turbojet section, through the implementation of of a new type of seal better adapted to the conditions of operation.
  • Another object of the invention is to propose a type of seal which simplify crankcase structure at the location of the zone to quench.
  • the invention achieves its goal by the fact that the seal is realized in the form of a ring annular ferrule having a first substantially cylindrical portion sealingly attached to a face of the axial wall and a second part extending said first part, and located in the space between said axial wall of said surface radial, said second part having, in section along a radial plane containing the axis of the turbojet, a V-shaped profile and having a portion end bearing slidingly and sealingly against said radial surface.
  • the proposed joint is thus in the form of a ring in sheet having a first cylindrical portion which is enclosed on the wall cylindrical inner casing, and a second part consisting of two conical portions connected together, and whose median portion is connected to the first cylindrical part, the free end of the other frustoconical portion being in sliding support on the radial surface of the outer casing.
  • the radial wall of the inner casing and the axial walls complementary to the two state-of-the-art housings no longer utility and can be deleted.
  • the first part of the seal can be fixed on the axial wall of the internal casing by riveting or bolting.
  • the first part preferably includes a redan which cooperates with a complementary projection formed on the adjacent face of the axial wall, which ensures the stop in axial translation of the seal relative to the inner casing.
  • the second part is placed in axial compression during assembly of the inner casing on the outer casing.
  • the end portion of the second part is curved so that its external axial face bears on said surface radial.
  • the seal according to the invention is configured in such a way that the pressure difference between high and low pressure regions positively the end portion of the second part to the surface radial.
  • the tip of the V-shaped section is arranged radially under the axial wall, and vice versa if the low pressure is radially outside the inner casing, the second part is disposed above the axial wall of the inner casing.
  • the seal according to the invention is particularly suitable for a high-pressure compressor of a turbojet, but it can also be used for other parts of a turbomachine, particularly at level of stator housings or turbine stators.
  • FIG 1 shows a stator 1 of a high compressor pressure, according to the state of the art, which equips a turbojet engine.
  • This stator 1 comprises an inner casing 2 and an outer casing 3 connected in upstream by bolting flanges 4 and 5 respectively provided on a annular wall 6 of the outer casing 3 and on an annular wall substantially axial 7 of the inner casing 2.
  • the annular wall 7 is extends downstream and its substantially cylindrical end 8 connected, facing a radial surface 9 integral with the outer casing 2, a second radial wall 10 connected itself to an axial wall complementary 11 which extends to the radial surface 9 of the housing 2.
  • the wall axial 11 and the second radial wall 10 houses a joint 13 Omega type which bears on the radial surface 9 of the outer casing 3 and on the face vis-à-vis the radial wall 10 of the inner housing 2.
  • a second axial wall 16 is provided on the outer casing 3 above the groove 12.
  • the Omega 13 seal is intended to seal between the enclosure 14 located under the outer casing 3, where there is a pressure P1, and the enclosure 15 located under the end 8 of the axial wall 7 where there is a pressure P2 less than the pressure P1.
  • Figures 2 and 3 show the changes made to the end 8 of the axial wall 7 and the new seal 20 proposed by the invention for sealing between the end 8 of the axial wall 7 of the inner casing 2 and the radial surface 9 of the outer casing 3.
  • the radial wall 10 and the axial wall complementary 11 have no more utility and can be totally eliminated, which facilitates the machining of the downstream end 8 of the wall 7.
  • the second axial wall 16 of the outer casing 3 can also be deleted.
  • the seal 20 is in the form of an annular ring in sheet metal having two parts 21 and 22 having distinct functions.
  • the first part 21 is substantially cylindrical and its diameter is equal to the outside diameter of the end portion 8 of the wall ring 7 of the inner casing 2, so that it can be fitted on this end portion 8.
  • the second part 22, which constitutes the seal seal itself, is arranged in the space 23 separating the end face 8a of the axial wall 7 and the radial surface 9, and present in section, in a radial plane containing the axis of the turbojet engine, a V-section or flared U-section
  • This second part 22 thus comprises two portions frustoconical 24 and 25 interconnected by a shaped portion 26 of annular gutter.
  • the medial frustoconical portion 24 is connected to the first part 21 by an annular portion 27 whose face convex 27a is located on the side of the chamber 14 in which there is a fluid at the pressure P1 and at the temperature t1, the pressure P1 being greater than the pressure P2 prevailing in the chamber 15 located under the wall axial 7 of the inner casing 2.
  • the other frustoconical portion 25 is slightly curved near its free end, so that its end portion 25a has on its opposite side to the first part 21 a convex annular surface in sliding support on the radial surface 9 of the outer casing 3.
  • the annular volume between the two portions frustoconical 24 and 25 is thus in the enclosure 14 at high pressure, and the pressure differences on both sides of the second part 22 tend to separate the frustoconical portion 24 of the frustoconical portion 25, which ensures the seal between the two enclosures 14 and 15, during the relative axial or radial displacements between the end 8 of the wall axial 7 and the radial surface 9 of the outer enclosure.
  • the first part 21 is fixed by brazing on the external face of the axial wall 7.
  • the first portion 21 advantageously has a redan 30 which cooperates with a complementary projection 31 formed on the outer face of the wall axial 7, to ensure a stop in translation of the seal 20.
  • the first part 21 of the seal 20 and the end 8 of the axial wall 7 of the casing inside 2 have corresponding holes for fastening the seal 20 on the end 8 of the axial wall by bolting or by riveting.
  • the second part 22 is put into compression when mounting the inner casing 2 on the outer casing 3.
  • the geometry of this second part 22 is calculated so as to provide significant flexibility.
  • the section of the seal 20 is sufficiently large to allow to absorb more relative displacements important than those allowed by the current Omega seal and allows the use of a thicker sheet, which reduces the impact to the wear of the faces in contact and makes the seal 20 more tolerant to vibration.

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

Abstract

The section has a joint formed in the shape of an annular sheet metal ring presenting a cylindrical part (21) fixed in a tight manner on a side of an axial wall (8) of an inner casing, and a part (22) extending the part (21). The part (22) is located in a space (23) separating the wall from a radial surface (9) of an outer casing. The part (22) has a V profile and an end portion (25a) in sliding and tight support against the surface.

Description

L'invention concerne l'étanchéité entre deux enceintes d'un turboréacteur délimitées par des carters et soumises à des pressions différentes.The invention relates to the sealing between two enclosures of a turbojet engine delimited by crankcases and subjected to pressure different.

Elle concerne plus précisément une section de turboréacteur comportant un carter extérieur ayant une surface qui s'étend radialement vers l'intérieur, un carter intérieur ayant une paroi sensiblement axiale qui s'étend vers ladite surface et un joint d'étanchéité disposé entre ladite paroi et ladite surface et destiné à assurer l'étanchéité entre les régions à haute et basse pressions situées de part et d'autre dudit joint.It concerns more specifically a turbojet section having an outer casing having a radially extending surface inward, an inner casing having a substantially axial wall which extends towards said surface and a seal disposed between said wall and said surface and intended to ensure the seal between the regions to high and low pressures located on either side of said seal.

Un turboréacteur comporte un canal annulaire dans lequel circule un fluide chaud de travail dont la température et la pression varient en fonction de la puissance demandée au moteur. Ces variations de température entraínent des dilatations des carters entourant le canal, et certaines pièces, notamment au niveau des turbines, soumises aux températures les plus élevées, nécessitent un refroidissement par un air frais sous haute pression. Le refroidissement est réalisé par un prélèvement d'air au niveau d'un étage du compresseur haute pression. Cet air de refroidissement circule dans des enceintes ménagées entre un carter extérieur et un carter intérieur des sections de compresseur et de turbines.A turbojet engine has an annular channel in which circulates a hot working fluid whose temperature and pressure vary depending on the power demanded from the motor. These variations of temperature causes dilation of the casings surrounding the channel, and certain parts, particularly at the turbine level, subject to highest temperatures require cooling with air fresh under high pressure. Cooling is carried out by a air sampling at a stage of the high pressure compressor. This cooling air circulates in enclosures arranged between a outer casing and an inner casing of the compressor and turbines.

Du fait des variations de charge, qui entraínent des variations de température et de dilatation des carters, des jeux sont prévus entre les extrémités des deux carters de chaque section, opposées aux extrémités fixées entre elles par boulonnage. Pour éviter les fuites, entre l'enceinte soumise à une haute pression et l'enceinte soumise à une pression plus faible, ce qui conduirait à une baisse de rendement du moteur, il est nécessaire d'étancher les jeux par des joints dilatables supportant les écarts de pression et de température entre les deux enceintes.Because of load variations, which lead to variations temperature and expansion of the casings, games are provided between ends of the two casings of each section, opposite to the ends fixed together by bolting. To avoid leaks, between the speaker subjected to high pressure and the enclosure subjected to more pressure low, which would lead to a decline in engine efficiency, it is necessary to seal the gaps with expansion joints supporting the pressure and temperature differences between the two speakers.

US 6 431 555 et US 6 464 457 montrent des joints annulaires constitués par une pluralité de segments à lamelles retenus par des broches sur le carter interne et maintenus en appui sur deux sièges respectifs des deux carters par des ressorts. Ces dispositions nécessitent beaucoup de main d'oeuvre au montage et des fuites peuvent encore se produire entre des lamelles voisines.US 6,431,555 and US 6,464,457 show annular seals constituted by a plurality of lamellar segments retained by pins on the inner housing and held in support on two seats respective of the two casings by springs. These provisions require a lot of assembly labor and leaks can still happen produce between adjacent lamellae.

Une autre technique employée dans un compresseur haute pression, montrée sur la figure 1, consiste à positionner entre deux surfaces radiales prévues, en vis à vis, l'une sur le carter extérieur et l'autre sur le carter intérieur, un joint annulaire de type Oméga qui se présente sous la forme d'un soufflet maintenu en compression entre lesdites deux surfaces.Another technique used in a high compressor pressure, shown in Figure 1, is to position between two radial surfaces provided, facing each other, one on the outer casing and the other on the inner casing, an Omega-type annular seal present in the form of a bellows maintained in compression between said two surfaces.

Du fait de déplacements relatifs importants en fonctionnement entre les deux carters formant la cavité du joint, dans des directions à la fois radiales et axiales, ce joint Oméga se dégrade rapidement et se fractionne en plusieurs morceaux. L'étanchéité n'est alors plus assurée de manière satisfaisante, ce qui peut entraíner un réchauffement de l'air de refroidissement de la turbine, et une modification des jeux radiaux pouvant dégrader la marge au pompage du compresseur.Due to significant relative movements in operation between the two housings forming the joint cavity, in directions to the both radial and axial, this Omega seal degrades rapidly and split into several pieces. The seal is no longer assured of satisfactorily, which can lead to a warming of the air of cooling of the turbine, and a modification of the radial clearances can degrade the compressor's pumping margin.

En outre, ce joint Oméga est maintenu radialement entre deux parois axiales complémentaires annulaires, formées l'une sur le carter intérieur et l'autre sur le carter extérieur, dont l'une au moins s'étend vers la surface radiale de l'autre carter et peut être soumise à des contraintes axiales dans certaines conditions de fonctionnement du turboréacteur. Ceci exige des opérations supplémentaires d'usinage pour réaliser ces parois axiales complémentaires qui, dans certaines conditions, empêchent une dilatation libre du carter intérieur par rapport au carter extérieur.In addition, this Omega seal is held radially between two annular complementary axial walls, formed one on the housing inside and the other on the outer casing, of which at least one extends the radial surface of the other housing and may be subject to constraints axial under certain operating conditions of the turbojet engine. This requires additional machining operations to achieve these complementary axial walls which, under certain conditions, prevent free expansion of the inner casing relative to the outer casing.

L'invention a pour premier but d'assurer une étanchéité pérenne entre deux carters d'une section de turboréacteur, par la mise en place d'un nouveau type de joint mieux adapté aux conditions de fonctionnement.The invention has the primary purpose of sealing between two casings of a turbojet section, through the implementation of of a new type of seal better adapted to the conditions of operation.

Un autre but de l'invention est de proposer un type de joint qui permette de simplifier la structure des carters à l'emplacement de la zone à étancher.Another object of the invention is to propose a type of seal which simplify crankcase structure at the location of the zone to quench.

L'invention atteint son but par le fait que le joint est réalisé sous la forme d'une virole annulaire en tôle présentant une première partie sensiblement cylindrique fixée de manière étanche sur une face de la paroi axiale et une deuxième partie prolongeant ladite première partie, et située dans l'espace séparant ladite paroi axiale de ladite surface radiale, ladite deuxième partie présentant, en coupe selon un plan radial contenant l'axe du turboréacteur, un profil en V et présentant une portion d'extrémité en appui coulissant et étanche contre ladite surface radiale.The invention achieves its goal by the fact that the seal is realized in the form of a ring annular ferrule having a first substantially cylindrical portion sealingly attached to a face of the axial wall and a second part extending said first part, and located in the space between said axial wall of said surface radial, said second part having, in section along a radial plane containing the axis of the turbojet, a V-shaped profile and having a portion end bearing slidingly and sealingly against said radial surface.

Le joint proposé se présente ainsi sous la forme d'un anneau en tôle ayant une première partie cylindrique qui s'emmanche sur la paroi cylindrique du carter intérieur, et une deuxième partie constituée par deux portions tronconiques raccordées entre elles, et dont la portion médiane est raccordée à la première partie cylindrique, l'extrémité libre de l'autre portion tronconique étant en appui coulissant sur la surface radiale du carter externe.The proposed joint is thus in the form of a ring in sheet having a first cylindrical portion which is enclosed on the wall cylindrical inner casing, and a second part consisting of two conical portions connected together, and whose median portion is connected to the first cylindrical part, the free end of the other frustoconical portion being in sliding support on the radial surface of the outer casing.

La paroi radiale du carter interne et les parois axiales complémentaires des deux carters de l'état de la technique n'ont plus d'utilité et peuvent être supprimées.The radial wall of the inner casing and the axial walls complementary to the two state-of-the-art housings no longer utility and can be deleted.

La première partie du joint peut être fixée sur la paroi axiale du carter interne par rivetage ou boulonnage.The first part of the seal can be fixed on the axial wall of the internal casing by riveting or bolting.

Elle peut avantageusement être fixée sur la paroi axiale du carter interne par brasage, ce qui améliore l'étanchéité dans cette zone. Dans ce cas, la première partie comporte de préférence un redan qui coopère avec un ressaut complémentaire formé sur la face adjacente de la paroi axiale, ce qui assure l'arrêt en translation axiale du joint par rapport au carter interne.It can advantageously be fixed on the axial wall of the internal casing by brazing, which improves the sealing in this area. In this case, the first part preferably includes a redan which cooperates with a complementary projection formed on the adjacent face of the axial wall, which ensures the stop in axial translation of the seal relative to the inner casing.

Pour assurer l'étanchéité dans toutes les conditions de vol, la deuxième partie est mise en compression axiale lors du montage du carter interne sur le carter externe.To ensure watertightness in all flight conditions, the second part is placed in axial compression during assembly of the inner casing on the outer casing.

Afin d'améliorer le coulissement radial du joint sur la surface radiale du carter externe, la portion d'extrémité de la deuxième partie est recourbée afin que sa face axiale externe soit en appui sur ladite surface radiale.In order to improve the radial sliding of the seal on the surface radially from the outer casing, the end portion of the second part is curved so that its external axial face bears on said surface radial.

Le joint selon l'invention est configuré de telle manière que la différence de pression entre les régions à haute et basse pressions sollicite positivement la portion d'extrémité de la deuxième partie vers la surface radiale. Autrement dit, si la région à haute pression est radialement à l'extérieur du carter interne, la pointe de la section en V est disposée radialement sous la paroi axiale, et inversement si la région à basse pression est radialement à l'extérieur du carter interne, la deuxième partie est disposée au-dessus de la paroi axiale du carter interne.The seal according to the invention is configured in such a way that the pressure difference between high and low pressure regions positively the end portion of the second part to the surface radial. In other words, if the high pressure region is radially the outside of the inner casing, the tip of the V-shaped section is arranged radially under the axial wall, and vice versa if the low pressure is radially outside the inner casing, the second part is disposed above the axial wall of the inner casing.

Le joint selon l'invention est particulièrement adapté pour un compresseur haute pression d'un turboréacteur, mais il peut également être utilisé pour d'autres pièces d'une turbomachine, notamment au niveau des carters de redresseurs ou des stators de turbine. The seal according to the invention is particularly suitable for a high-pressure compressor of a turbojet, but it can also be used for other parts of a turbomachine, particularly at level of stator housings or turbine stators.

D'autres avantages et caractéristiques de l'invention ressortiront à la lecture de la description suivante, faite à titre d'exemple et en référence aux dessins annexés dans lesquels :

  • la figure 1 montre, en coupe, un compresseur haute pression d'un turboréacteur comportant un joint d'étanchéité, selon l'état de la technique, entre un carter interne et un carter externe ;
  • la figure 2 montre, en coupe, le même compresseur équipé d'un joint selon une premier mode de réalisation de l'invention ; et
  • la figure 3 montre un deuxième mode de réalisation de l'invention.
    • Other advantages and characteristics of the invention will emerge on reading the following description, given by way of example and with reference to the appended drawings, in which:
  • Figure 1 shows, in section, a high pressure compressor of a turbojet engine comprising a seal, according to the state of the art, between an inner housing and an outer casing;
  • Figure 2 shows, in section, the same compressor equipped with a seal according to a first embodiment of the invention; and
  • Figure 3 shows a second embodiment of the invention.

    • La figure 1 montre un stator 1 d'un compresseur haute pression, selon l'état de la technique, qui équipe un turboréacteur. Ce stator 1 comporte un carter intérieur 2 et un carter extérieur 3 reliés en amont par boulonnage de brides 4 et 5 prévues respectivement sur une paroi annulaire 6 du carter extérieur 3 et sur une paroi annulaire sensiblement axiale 7 du carter intérieur 2. La paroi annulaire 7 se prolonge vers l'aval et son extrémité 8 sensiblement cylindrique se raccorde, en regard d'une surface radiale 9 solidaire du carter extérieur 2, à une deuxième paroi radiale 10 raccordée elle-même à une paroi axiale complémentaire 11 qui s'étend jusqu'à la surface radiale 9 du carter extérieur 2. Dans la rainure 12, délimitée par la surface radiale 9, la paroi axiale 11 et la deuxième paroi radiale 10, loge un joint 13 de type Oméga qui est en appui sur la surface radiale 9 du carter extérieur 3 et sur la face en vis-à-vis de la paroi radiale 10 du carter intérieur 2. Une deuxième paroi axiale 16 est prévue sur le carter extérieur 3 au-dessus de la rainure 12.Figure 1 shows a stator 1 of a high compressor pressure, according to the state of the art, which equips a turbojet engine. This stator 1 comprises an inner casing 2 and an outer casing 3 connected in upstream by bolting flanges 4 and 5 respectively provided on a annular wall 6 of the outer casing 3 and on an annular wall substantially axial 7 of the inner casing 2. The annular wall 7 is extends downstream and its substantially cylindrical end 8 connected, facing a radial surface 9 integral with the outer casing 2, a second radial wall 10 connected itself to an axial wall complementary 11 which extends to the radial surface 9 of the housing 2. In the groove 12, delimited by the radial surface 9, the wall axial 11 and the second radial wall 10, houses a joint 13 Omega type which bears on the radial surface 9 of the outer casing 3 and on the face vis-à-vis the radial wall 10 of the inner housing 2. A second axial wall 16 is provided on the outer casing 3 above the groove 12.

    Le joint Oméga 13 est destiné à assurer l'étanchéité entre l'enceinte 14 située sous le carter extérieur 3, où règne une pression P1, et l'enceinte 15 située sous l'extrémité 8 de la paroi axiale 7 où règne une pression P2 inférieure à la pression P1.The Omega 13 seal is intended to seal between the enclosure 14 located under the outer casing 3, where there is a pressure P1, and the enclosure 15 located under the end 8 of the axial wall 7 where there is a pressure P2 less than the pressure P1.

    Les figures 2 et 3 montrent les modifications apportées à l'extrémité 8 de la paroi axiale 7 et le nouveau joint 20 proposé par l'invention pour assurer l'étanchéité entre l'extrémité 8 de la paroi axiale 7 du carter intérieur 2 et la surface radiale 9 du carter extérieur 3.Figures 2 and 3 show the changes made to the end 8 of the axial wall 7 and the new seal 20 proposed by the invention for sealing between the end 8 of the axial wall 7 of the inner casing 2 and the radial surface 9 of the outer casing 3.

    Selon l'invention, la paroi radiale 10 et la paroi axiale complémentaire 11, n'ont plus d'utilité et peuvent être totalement éliminées, ce qui facilite l'usinage de l'extrémité aval 8 de la paroi annulaire 7. La deuxième paroi axiale 16 du carter externe 3 peut également être supprimée.According to the invention, the radial wall 10 and the axial wall complementary 11, have no more utility and can be totally eliminated, which facilitates the machining of the downstream end 8 of the wall 7. The second axial wall 16 of the outer casing 3 can also be deleted.

    Le joint 20 se présente sous la forme d'une virole annulaire en tôle comportant deux parties 21 et 22 ayant des fonctions distinctes. La première partie 21 est sensiblement cylindrique et son diamètre est égal au diamètre extérieur de la portion d'extrémité 8 de la paroi annulaire 7 du carter intérieur 2, afin qu'elle puisse être emmanchée sur cette portion d'extrémité 8. La deuxième partie 22, qui constitue le joint d'étanchéité proprement dit, est disposée dans l'espace 23 séparant la face d'extrémité 8a de la paroi axiale 7 et la surface radiale 9, et présente en coupe, selon un plan radial contenant l'axe du turboréacteur, une section en V ou en U évaséThe seal 20 is in the form of an annular ring in sheet metal having two parts 21 and 22 having distinct functions. The first part 21 is substantially cylindrical and its diameter is equal to the outside diameter of the end portion 8 of the wall ring 7 of the inner casing 2, so that it can be fitted on this end portion 8. The second part 22, which constitutes the seal seal itself, is arranged in the space 23 separating the end face 8a of the axial wall 7 and the radial surface 9, and present in section, in a radial plane containing the axis of the turbojet engine, a V-section or flared U-section

    Cette deuxième partie 22 comporte ainsi deux portions tronconiques 24 et 25 raccordées entre elles par une portion 26 en forme de gouttière annulaire. La portion tronconique médiane 24 est raccordée à la première partie 21 par une portion annulaire 27 dont la face convexe 27a est située du côté de l'enceinte 14 dans laquelle règne un fluide à la pression P1 et à la température t1, la pression P1 étant supérieure à la pression P2 régnant dans l'enceinte 15 située sous la paroi axiale 7 du carter intérieur 2.This second part 22 thus comprises two portions frustoconical 24 and 25 interconnected by a shaped portion 26 of annular gutter. The medial frustoconical portion 24 is connected to the first part 21 by an annular portion 27 whose face convex 27a is located on the side of the chamber 14 in which there is a fluid at the pressure P1 and at the temperature t1, the pressure P1 being greater than the pressure P2 prevailing in the chamber 15 located under the wall axial 7 of the inner casing 2.

    L'autre portion tronconique 25 est légèrement recourbée près de son extrémité libre, afin que sa portion d'extrémité 25a présente sur sa face opposée à la première partie 21 une surface annulaire convexe en appui coulissant sur la surface radiale 9 du carter extérieur 3.The other frustoconical portion 25 is slightly curved near its free end, so that its end portion 25a has on its opposite side to the first part 21 a convex annular surface in sliding support on the radial surface 9 of the outer casing 3.

    Le volume annulaire situé entre les deux portions tronconiques 24 et 25 se trouve ainsi dans l'enceinte 14 à haute pression, et les différences de pression sur les deux faces de la deuxième partie 22 tendent à écarter la portion tronconique 24 de la portion tronconique 25, ce qui assure l'étanchéité entre les deux enceintes 14 et 15, lors des déplacements axiaux ou radiaux relatifs entre l'extrémité 8 de la paroi axiale 7 et la surface radiale 9 de l'enceinte extérieure.The annular volume between the two portions frustoconical 24 and 25 is thus in the enclosure 14 at high pressure, and the pressure differences on both sides of the second part 22 tend to separate the frustoconical portion 24 of the frustoconical portion 25, which ensures the seal between the two enclosures 14 and 15, during the relative axial or radial displacements between the end 8 of the wall axial 7 and the radial surface 9 of the outer enclosure.

    Dans le mode de réalisation montré sur la figure 2, la première partie 21 est fixée par brasage sur la face externe de la paroi axiale 7. La première partie 21 présente avantageusement un redan 30 qui coopère avec un ressaut complémentaire 31 formé sur la face externe de la paroi axiale 7, pour assurer un arrêt en translation du joint 20.In the embodiment shown in Figure 2, the first part 21 is fixed by brazing on the external face of the axial wall 7. The first portion 21 advantageously has a redan 30 which cooperates with a complementary projection 31 formed on the outer face of the wall axial 7, to ensure a stop in translation of the seal 20.

    Dans le mode de réalisation montré sur la figure 3, la première partie 21 du joint 20 et l'extrémité 8 de la paroi axiale 7 du carter intérieur 2 présentent en correspondance des orifices pour la fixation du joint 20 sur l'extrémité 8 de la paroi axiale par boulonnage ou par rivetage.In the embodiment shown in Figure 3, the first part 21 of the seal 20 and the end 8 of the axial wall 7 of the casing inside 2 have corresponding holes for fastening the seal 20 on the end 8 of the axial wall by bolting or by riveting.

    Quel que soit le mode de réalisation de la fixation du joint 20 sur le carter intérieur 2, la deuxième partie 22 est mise en compression lors du montage du carter intérieur 2 sur le carter extérieur 3. La géométrie de cette deuxième partie 22 est calculée de manière à assurer une souplesse importante. La section du joint 20 est suffisamment grande pour permettre d'absorber des déplacements relatifs plus importants que ceux autorisés par le joint Oméga actuel et permet l'utilisation d'une tôle d'épaisseur plus importante, ce qui diminue l'impact à l'usure au droit des faces en contact et rend le joint 20 plus tolérant aux vibrations.Whatever the embodiment of the attachment of the seal 20 on the inner casing 2, the second part 22 is put into compression when mounting the inner casing 2 on the outer casing 3. The geometry of this second part 22 is calculated so as to provide significant flexibility. The section of the seal 20 is sufficiently large to allow to absorb more relative displacements important than those allowed by the current Omega seal and allows the use of a thicker sheet, which reduces the impact to the wear of the faces in contact and makes the seal 20 more tolerant to vibration.

    Claims (9)

    Section de turboréacteur comportant un carter externe (3) ayant une surface (9) qui s'étend radialement vers l'intérieur, un carter interne (2) ayant une paroi (8) sensiblement axiale qui s'étend vers ladite surface (9), et un joint d'étanchéité (20) disposé entre ladite paroi (8) et ladite surface (9) et destiné à assurer l'étanchéité entre les régions (14, 15) à haute et basse pressions situés de part et d'autre dudit joint (20),
       caractérisée par le fait que ledit joint est réalisé sous la forme d'une virole annulaire en tôle présentant une première partie (21) sensiblement cylindrique fixée de manière étanche sur une face de la paroi axiale (8) et une deuxième partie (22) prolongeant ladite première partie et située dans l'espace (23) séparant ladite paroi axiale (8) de ladite surface radiale (9), ladite deuxième partie présentant, en coupe selon un plan radial contenant l'axe du turboréacteur, un profil en V et présentant une portion d'extrémité (25a) en appui coulissant et étanche contre ladite surface radiale (9).    Turbojet section comprising an outer casing (3) having a surface (9) extending radially inwardly, an inner casing (2) having a substantially axial wall (8) extending towards said surface (9) , and a seal (20) disposed between said wall (8) and said surface (9) and intended to seal between the regions (14, 15) at high and low pressure located on either side said seal (20),
    characterized in that said seal is in the form of an annular ferrule made of sheet metal having a substantially cylindrical first portion (21) sealingly attached to one face of the axial wall (8) and a second portion (22) extending said first portion and located in the space (23) separating said axial wall (8) from said radial surface (9), said second portion having, in section along a radial plane containing the axis of the turbojet, a V-shaped profile and having an end portion (25a) slidingly and sealingly against said radial surface (9).         Section de turboréacteur selon la revendication 1, caractérisée par le fait que la première partie (21) est fixée sur la paroi axiale (8) par rivetage ou boulonnage.Turbojet section according to claim 1, characterized in that the first portion (21) is fixed on the axial wall (8) by riveting or bolting. Section de turboréacteur selon la revendication 1, caractérisée par le fait que la première partie (21) est fixée sur la paroi axiale (8) par brasage.Turbojet section according to claim 1, characterized in that the first portion (21) is fixed to the axial wall (8) by brazing. Section de turboréacteur selon la revendication 3, caractérisée par le fait que la première partie (21) comporte un redan (30) coopérant avec un ressaut (31) complémentaire formé sur la face adjacente de la paroi axiale (8).Turbojet section according to claim 3, characterized in that the first portion (21) comprises a step (30) cooperating with a complementary projection (31) formed on the adjacent face of the axial wall (8). Section de turboréacteur selon l'une quelconque des revendications 1 à 4, caractérisée par le fait que la deuxième partie (22) est mise en compression axiale lors du montage du carter interne (2) sur le carter externe (3).Turbojet section according to any one of claims 1 to 4, characterized in that the second portion (22) is placed in axial compression during assembly of the inner casing (2) on the outer casing (3). Section de turboréacteur selon l'une quelconque des revendications 1 à 5, caractérisée par le fait que la portion d'extrémité (25a) de la deuxième partie (22) est recourbée afin que sa face axialement externe soit en appui sur la surface radiale (9). Turbojet section according to any one of claims 1 to 5, characterized in that the end portion (25a) of the second portion (22) is bent so that its axially outer face bears on the radial surface ( 9). Section de turboréacteur selon l'une quelconque des revendications 1 à 5, caractérisée par le fait que le joint (20) est configuré de telle manière que la différence de pression entre les régions (14, 15) à haute et basse pressions sollicite la portion d'extrémité (25a) de la deuxième partie (22) vers la surface radiale (9).Turbojet section according to any one of claims 1 to 5, characterized in that the seal (20) is configured in such a way that the pressure difference between the regions (14, 15) at high and low pressures solicits the portion end portion (25a) of the second portion (22) to the radial surface (9). Section de turboréacteur selon la revendication 7, caractérisée par le fait que la première partie (21) est appliquée sur la face de la paroi axiale (8) soumise à la haute pression.Turbojet section according to claim 7, characterized in that the first portion (21) is applied to the face of the axial wall (8) subjected to high pressure. Section de turboréacteur selon l'une quelconque des revendications 1 à 8, caractérisée par le fait que ladite section est un compresseur à haute pression.Turbojet section according to any one of claims 1 to 8, characterized in that said section is a high pressure compressor.
    EP05290664A 2004-03-26 2005-03-25 Annular sheet metal seal for sealing the space between an inner and an outer turbomachine casing Withdrawn EP1580403A1 (en)

    Applications Claiming Priority (2)

    Application Number Priority Date Filing Date Title
    FR0403130 2004-03-26
    FR0403130A FR2868119B1 (en) 2004-03-26 2004-03-26 SEAL SEAL BETWEEN THE INTERIOR AND EXTERIOR HOUSINGS OF A TURBOJET SECTION

    Publications (1)

    Publication Number Publication Date
    EP1580403A1 true EP1580403A1 (en) 2005-09-28

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    EP05290664A Withdrawn EP1580403A1 (en) 2004-03-26 2005-03-25 Annular sheet metal seal for sealing the space between an inner and an outer turbomachine casing

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    US (1) US20050242522A1 (en)
    EP (1) EP1580403A1 (en)
    JP (1) JP2005282571A (en)
    CA (1) CA2500965A1 (en)
    FR (1) FR2868119B1 (en)
    RU (1) RU2005108415A (en)

    Cited By (1)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    FR3027874A1 (en) * 2014-11-03 2016-05-06 Airbus Operations Sas PROPULSION ASSEMBLY COMPRISING A JOINT

    Families Citing this family (10)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    FR2938873B1 (en) * 2008-11-21 2014-06-27 Turbomeca POSITIONING DEVICE FOR RING SEGMENT
    EP2530249A1 (en) 2011-05-30 2012-12-05 Siemens Aktiengesellschaft Piston seal ring
    US9017015B2 (en) * 2011-10-27 2015-04-28 General Electric Company Turbomachine including an inner-to-outer turbine casing seal assembly and method
    FR2986836B1 (en) * 2012-02-09 2016-01-01 Snecma ANTI-WEAR ANNULAR TOOL FOR A TURBOMACHINE
    EP2938834A1 (en) * 2012-12-29 2015-11-04 United Technologies Corporation Bumper for seals in a turbine exhaust case
    WO2014133616A1 (en) * 2013-03-01 2014-09-04 Rolls-Royce North American Technologies,Inc. Gas turbine engine impeller system for an intermediate pressure (ip) compressor
    WO2014137430A1 (en) * 2013-03-08 2014-09-12 Rolls-Royce North American Technologies, Inc. Gas turbine engine centrifugal compressor with seal between two diffuser parts
    US10184354B2 (en) * 2013-06-19 2019-01-22 United Technologies Corporation Windback heat shield
    CN110318829A (en) * 2019-07-19 2019-10-11 中国航发沈阳发动机研究所 A kind of elastic piece seal structure
    CN115405370B (en) * 2022-11-03 2023-03-10 中国航发沈阳发动机研究所 Semi-elastic turbine outer ring structure

    Citations (9)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    FR2468738A1 (en) * 1979-11-01 1981-05-08 United Technologies Corp SEALING ORGAN FOR A GAS TURBINE
    US4336943A (en) * 1980-11-14 1982-06-29 United Technologies Corporation Wedge-shaped seal for flanged joints
    EP0177650A1 (en) * 1983-08-22 1986-04-16 Heat Transfer Technology Limited Cylinder end seal
    WO1998053228A1 (en) * 1997-05-21 1998-11-26 Allison Advanced Development Company Interstage vane seal apparatus
    US6164656A (en) * 1999-01-29 2000-12-26 General Electric Company Turbine nozzle interface seal and methods
    EP1130219A1 (en) * 2000-03-02 2001-09-05 Siemens Aktiengesellschaft Turbine engine with sealing means between panels
    US6568903B1 (en) * 2001-12-28 2003-05-27 General Electric Company Supplemental seal for the chordal hinge seals in a gas turbine
    US20040031271A1 (en) * 2002-08-15 2004-02-19 Power Systems Mfg, Llc Convoluted seal with enhanced wear capability
    EP1515003A1 (en) * 2003-09-11 2005-03-16 Siemens Aktiengesellschaft Gas turbine and sealing means for a gas turbine

    Family Cites Families (5)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    US4199151A (en) * 1978-08-14 1980-04-22 General Electric Company Method and apparatus for retaining seals
    US4477086A (en) * 1982-11-01 1984-10-16 United Technologies Corporation Seal ring with slidable inner element bridging circumferential gap
    US5149250A (en) * 1991-02-28 1992-09-22 General Electric Company Gas turbine vane assembly seal and support system
    CA2070511C (en) * 1991-07-22 2001-08-21 Steven Milo Toborg Turbine nozzle support
    US5562408A (en) * 1995-06-06 1996-10-08 General Electric Company Isolated turbine shroud

    Patent Citations (9)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    FR2468738A1 (en) * 1979-11-01 1981-05-08 United Technologies Corp SEALING ORGAN FOR A GAS TURBINE
    US4336943A (en) * 1980-11-14 1982-06-29 United Technologies Corporation Wedge-shaped seal for flanged joints
    EP0177650A1 (en) * 1983-08-22 1986-04-16 Heat Transfer Technology Limited Cylinder end seal
    WO1998053228A1 (en) * 1997-05-21 1998-11-26 Allison Advanced Development Company Interstage vane seal apparatus
    US6164656A (en) * 1999-01-29 2000-12-26 General Electric Company Turbine nozzle interface seal and methods
    EP1130219A1 (en) * 2000-03-02 2001-09-05 Siemens Aktiengesellschaft Turbine engine with sealing means between panels
    US6568903B1 (en) * 2001-12-28 2003-05-27 General Electric Company Supplemental seal for the chordal hinge seals in a gas turbine
    US20040031271A1 (en) * 2002-08-15 2004-02-19 Power Systems Mfg, Llc Convoluted seal with enhanced wear capability
    EP1515003A1 (en) * 2003-09-11 2005-03-16 Siemens Aktiengesellschaft Gas turbine and sealing means for a gas turbine

    Cited By (1)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    FR3027874A1 (en) * 2014-11-03 2016-05-06 Airbus Operations Sas PROPULSION ASSEMBLY COMPRISING A JOINT

    Also Published As

    Publication number Publication date
    FR2868119B1 (en) 2006-06-16
    RU2005108415A (en) 2006-09-27
    US20050242522A1 (en) 2005-11-03
    FR2868119A1 (en) 2005-09-30
    JP2005282571A (en) 2005-10-13
    CA2500965A1 (en) 2005-09-26

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