EP0657624B1 - Turbine housing containing a sealing body - Google Patents

Turbine housing containing a sealing body Download PDF

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Publication number
EP0657624B1
EP0657624B1 EP19940402807 EP94402807A EP0657624B1 EP 0657624 B1 EP0657624 B1 EP 0657624B1 EP 19940402807 EP19940402807 EP 19940402807 EP 94402807 A EP94402807 A EP 94402807A EP 0657624 B1 EP0657624 B1 EP 0657624B1
Authority
EP
European Patent Office
Prior art keywords
casing
sealing body
flanges
turbomachine
flexible envelope
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.)
Expired - Lifetime
Application number
EP19940402807
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German (de)
French (fr)
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EP0657624A1 (en
Inventor
Jean Christian Henri Cattaneo
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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Application filed by Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0657624A1 publication Critical patent/EP0657624A1/en
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Publication of EP0657624B1 publication Critical patent/EP0657624B1/en
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Classifications

    • 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
    • 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 a wall of turbomachine comprising a sealing body.
  • turbomachine walls used for aircraft engines include in particular a outer casing which ensures cohesion by its rigidity of the assembly and an internal ferrule, concentric with the casing and formed of annular segments assembled to it and between them, which serve to delimit the vein gas flow.
  • FR-A-1 235 694 a firewall seal disposed between two assembly flanges and comprising an internal fiberfill, compressible and an envelope flexible deformable.
  • the casing, the ferrule and the flanges transverse assembly of the segments to the casing then delimit empty partitioned volumes which are the seat of gas leaks that affect good performance of the machine.
  • these often very hot gases produce radial thermal expansions and longitudinal on the casing, which affect the ferrule and therefore increase the radial clearances between the ferrule and the free ends of the rotor blades.
  • a larger part of the gas flow escapes the compression by the blades, then in the drive of the rotor while relaxing. So we are in front of a second because of lower yield.
  • the object of the invention which is to fill totally or almost these empty form volumes often tormented, is reached by housing bodies sealing formed of a flexible envelope and little breathable and insulating fluff material thermally and contained in the flexible envelope.
  • the flexibility of the envelope and fill, attached to the compressibility of the latter, allow the body sealing to be molded on the surfaces of the housing, ferrule segments, or even flanges, which virtually eliminates gas leaks.
  • the turbomachine is shown at the location of a high pressure compressor where the invention should find the most utility. It has a housing 1 exterior whose outer surface carries a certain number of bosses 2 circular in which we have drilled 3 oblique bolt holes. The internal surface of the casing 1 is smooth opposite the bosses 2, to that flanges 4 of ferrule segments 5 can be there to press. The flanges 4 are also provided with holes for bolt 6, which are an extension of those 3 of bosses 2, and bolts 7 are inserted therein retain the flanges 4 in place, with a component radial force which applies them to the surface of the housing 1 and an axial component that allows them to block seals 8 against shoulders 9 of the casing 1.
  • the essential element of the seals 8 is not the ring rigid which is thus compressed and serves as their reinforcement, but a thin and oblique veil 10, one end of which is embedded in the ring and the other end, free, is supported on the segmented flange 4 to cover the bolt holes 6 and recesses 11 made over a large part of their extension so that the flanges 4 do not rest actually on the casing 1 only by a small part of their circumference, which avoids transmissions excessive heat and reduces the risk of jamming during assembly.
  • the shell segments 5 delimit by outside an annular gas flow stream 14. They must form such a continuous surface and as regular as possible to avoid leaks and pressure losses and they are juxtaposed by different kinds of joints but some of them can be assembled by sockets 15 of a lip one in a throat of the other.
  • Certain shell segments 5 bear vanes 16 for rectifying the gas flow, which are arranged in stages alternating with stages movable blades 17 fixed to the rotor 18.
  • Games 19 extend between the ferrule segments 5 and the vanes mobile 17, and we want them to be as small as possible in order to avoid an appreciable portion gases do not flow there. That’s why we designed many devices, not shown here but which are extensively described and the subject of many patents, to control the value of games 19 to everyone machine speeds: these are blowing of gas taken from another part of the machine to adjust the thermal expansions of the shell segments 5.
  • This harmful flow is prohibited (figure 2) by means of a compound sealing body 25 essentially of a flock 26 contained in a flexible envelope 27 and which occupies all or almost of these empty volumes 20 thanks to the flexibility of the sealing body 25 and the compressibility of the wad 26, which deform under the action of surrounding pressure differences and espouse shapes of the cavity 20.
  • the materials used and especially those of the flock 26 are bad conductors heat and not very breathable, while being sufficiently porous that the compressibility of the fill 26 is not compromised.
  • Wad 26 can have a fibrous structure, and the envelope 27 be formed of a fabric.
  • the fiber can be quartz wool or metallic felts, and the fabric can be a intertwining of quartz, glass, carbon wires or metal.
  • Figure 3 shows a design a little different where the sealing body, referenced then 125 and still consisting of a flock 26 contained in a flexible envelope 27, is completed by a spring 28 of circular extension and whose cross section and linear and forms an acute angle, or a pin open: it consists of two sheets 29 substantially rigid than an elastic hinge 30 connects, and the volume 31 enclosed by the sheets 29 is empty.
  • the spring 28 is compressed, so that the sheets 29 tend to move apart, opening the spring 28, and the flock 26 is driven outwards and driven back against the surfaces of housing 1 and ferrule segments 5, including in their crevices.
  • Figure 4 shows the body seal 125 in an isolated state. It is manufactured under shape of a rod whose desired length is cut and that we roll to form a ring whose ends can be closed, or even joined between them by a seam, a weld or any other suitable means for envelope 27. If the sheets 29 are elastic and therefore have a certain stiffness, however, they should be flexible enough to be bent.

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

Description

L'invention se rapporte à une paroi de turbomachine comprenant un corps d'étanchéité.The invention relates to a wall of turbomachine comprising a sealing body.

Les parois de turbomachine utilisées pour les moteurs d'avion comprennent en particulier un carter extérieur qui assure par sa rigidité la cohésion de l'ensemble et une virole interne, concentrique au carter et formée de segments annulaires assemblés à lui et entre eux, qui servent à délimiter la veine d'écoulement des gaz.The turbomachine walls used for aircraft engines include in particular a outer casing which ensures cohesion by its rigidity of the assembly and an internal ferrule, concentric with the casing and formed of annular segments assembled to it and between them, which serve to delimit the vein gas flow.

Par ailleurs, on connaít par FR-A-1 235 694 un joint pare-feu disposé entre deux brides d'assemblage et comprenant une bourre interne en fibres, compressible et une enveloppe souple déformable.In addition, we know from FR-A-1 235 694 a firewall seal disposed between two assembly flanges and comprising an internal fiberfill, compressible and an envelope flexible deformable.

Le carter, la virole et les brides transversales d'assemblage des segments au carter délimitent alors des volumes vides cloisonnés qui sont le siège de fuites de gaz qui nuisent au bon rendement de la machine. De plus, ces gaz souvent très chauds produisent des dilatations thermiques radiales et longitudinales sur le carter, qui se répercutent sur la virole et accroissent donc les jeux radiaux entre la virole et les extrémités libres des aubes du rotor. Une partie plus importante du débit des gaz échappe à la compression par les aubes, puis à l'entraínement du rotor en se détendant. On est donc devant une deuxième cause d'abaissement du rendement.The casing, the ferrule and the flanges transverse assembly of the segments to the casing then delimit empty partitioned volumes which are the seat of gas leaks that affect good performance of the machine. In addition, these often very hot gases produce radial thermal expansions and longitudinal on the casing, which affect the ferrule and therefore increase the radial clearances between the ferrule and the free ends of the rotor blades. A larger part of the gas flow escapes the compression by the blades, then in the drive of the rotor while relaxing. So we are in front of a second because of lower yield.

Il a déjà été proposé de combler les volumes vides avec des matières d'isolation thermique, mais on n'a apparemment jamais proposé que des blocs ou des anneaux rigides ou semi-rigide de matière isolante, de résine par exemple, qui laissent subsister des intervalles par lesquels les fuites subsistent, et, dans une certaine mesure, les problèmes de défaut d'étanchéité évoqués plus haut.It has already been proposed to fill the empty volumes with thermal insulation materials, but apparently only blocks or rigid or semi-rigid rings of insulating material, resin for example, which leave intervals at which leaks persist, and, to some extent, default problems sealing mentioned above.

L'objet de l'invention, qui est de combler totalement ou presque ces volumes vides de forme souvent tourmentée, est atteint en y logeant des corps d'étanchéité formés d'une enveloppe souple et peu perméable à l'air et d'une matière en bourre isolante thermiquement et contenue dans l'enveloppe souple. La souplesse de l'enveloppe et de la bourre, jointe à la compressibilité de cette dernière, permettent au corps d'étanchéité de se mouler sur les surfaces du carter, des segments de virole, voire des brides, ce qui élimine à peu près complètement les fuites de gaz.The object of the invention, which is to fill totally or almost these empty form volumes often tormented, is reached by housing bodies sealing formed of a flexible envelope and little breathable and insulating fluff material thermally and contained in the flexible envelope. The flexibility of the envelope and fill, attached to the compressibility of the latter, allow the body sealing to be molded on the surfaces of the housing, ferrule segments, or even flanges, which virtually eliminates gas leaks.

Certains modes concrets de réalisation de l'invention vont maintenant être décrits à l'aide des figures suivantes annexées à titre illustratif et non limitatif :

  • la figure 1 est une vue générale d'une portion de turbomachine où l'élément constitutif de l'invention n'est pas représenté,
  • la figure 2 représente une première réalisation de l'invention,
  • la figure 3 représente une autre réalisation de l'invention,
  • et la figure 4 représente isolément le corps d'étanchéité de la seconde réalisation.
Certain concrete embodiments of the invention will now be described with the aid of the following figures, which are given by way of illustration and not limitation:
  • FIG. 1 is a general view of a portion of a turbomachine where the constituent element of the invention is not shown,
  • FIG. 2 represents a first embodiment of the invention,
  • FIG. 3 represents another embodiment of the invention,
  • and FIG. 4 represents the sealing body of the second embodiment in isolation.

On commence par le commentaire de la figure 1. La turbomachine est représentée à l'endroit d'un compresseur à haute pression, où l'invention devrait trouver le plus d'utilité. Elle comporte un carter 1 extérieur dont la surface externe porte un certain nombre de bossages 2 circulaires dans lesquels on a foré des trous de boulon 3 obliques. La surface interne du carter 1 est lisse à l'opposé des bossages 2, pour que des brides 4 de segments de virole 5 puissent s'y appuyer. Les brides 4 sont également munies de trous de boulon 6, qui viennent en prolongement de ceux 3 des bossages 2, et des boulons 7 y sont insérés pour retenir les brides 4 en place, avec une composante radiale d'effort qui les applique sur la surface du carter 1 et une composante axiale qui leur permet de bloquer des joints d'étanchéités 8 contre des épaulements 9 du carter 1. L'élément essentiel des joints d'étanchéité 8 n'est cependant pas l'anneau rigide qui est ainsi comprimé et leur sert d'armature, mais un voile 10 mince et oblique dont une extrémité est encastrée dans l'anneau et l'autre extrémité, libre, est appuyée sur la bride segmentée 4 correspondante pour recouvrir les trous de boulon 6 et des évidements 11 ménagés sur une grande partie de leur extension pour que les brides 4 ne s'appuient effectivement sur le carter 1 que par une petite partie de leur circonférence, ce qui évite les transmissions de chaleur excessives et diminue les risques de coincement pendant le montage. On prévoit alors des boulons supplémentaires 12 pour compléter le serrage des joints d'étanchéité 8 en appliquant des écrous 13 de forme particulière sur eux et sur la paroi du carter 1.We start with the commentary on the figure 1. The turbomachine is shown at the location of a high pressure compressor where the invention should find the most utility. It has a housing 1 exterior whose outer surface carries a certain number of bosses 2 circular in which we have drilled 3 oblique bolt holes. The internal surface of the casing 1 is smooth opposite the bosses 2, to that flanges 4 of ferrule segments 5 can be there to press. The flanges 4 are also provided with holes for bolt 6, which are an extension of those 3 of bosses 2, and bolts 7 are inserted therein retain the flanges 4 in place, with a component radial force which applies them to the surface of the housing 1 and an axial component that allows them to block seals 8 against shoulders 9 of the casing 1. The essential element of the seals 8 however is not the ring rigid which is thus compressed and serves as their reinforcement, but a thin and oblique veil 10, one end of which is embedded in the ring and the other end, free, is supported on the segmented flange 4 to cover the bolt holes 6 and recesses 11 made over a large part of their extension so that the flanges 4 do not rest actually on the casing 1 only by a small part of their circumference, which avoids transmissions excessive heat and reduces the risk of jamming during assembly. We then plan additional bolts 12 to complete the tightening seals 8 by applying nuts 13 of particular shape on them and on the casing wall 1.

Les segments de virole 5 délimitent par l'extérieur une veine annulaire d'écoulement des gaz 14. Ils doivent former une surface aussi continue et régulière que possible pour éviter les fuites et les pertes de charge et ils sont juxtaposés par différents genres de joints, mais certains d'entre eux peuvent être assemblés par des emboítements 15 d'une lèvre de l'un dans une gorge de l'autre.The shell segments 5 delimit by outside an annular gas flow stream 14. They must form such a continuous surface and as regular as possible to avoid leaks and pressure losses and they are juxtaposed by different kinds of joints but some of them can be assembled by sockets 15 of a lip one in a throat of the other.

Certains segments de virole 5 portent des aubes 16 de redressement de l'écoulement des gaz, qui sont disposées par étages alternant avec des étages d'aubes mobiles 17 fixées au rotor 18. Des jeux 19 s'étendent entre les segments de virole 5 et les aubes mobiles 17, et on souhaite qu'ils soient aussi petits que possible afin d'éviter qu'une portion appréciable des gaz ne s'y écoule. C'est pourquoi on a conçu de nombreux dispositifs, non représentés ici mais qui sont abondamment décrits et font le sujet de nombreux brevets, pour commander la valeur des jeux 19 à tous les régimes de la machine : il s'agit de dispositifs de soufflage de gaz prélevé d'une autre partie de la machine afin de régler les dilatations thermiques des segments de virole 5. Mais ces précautions sont quelque peu compromises par les fuites de gaz qui se glisse, à travers les intervalles des segments de virole 5 et par les jeux résiduels entre les brides 4, les voiles 10 et les emboitements 15, dans les volumes vides 20 délimités intérieurement par les segments de virole 5, extérieurement par le carter 1 et axialement par les brides 4, les écrous des boulons 7 et 12 et les joints 8. Les fuites d'air tendent à former un écoulement à contre-courant de l'écoulement dans la veine 14 et qui échauffe excessivement le carter 1, ce qui le dilate localement ainsi que les portions adjacentes des segments de virole 5.Certain shell segments 5 bear vanes 16 for rectifying the gas flow, which are arranged in stages alternating with stages movable blades 17 fixed to the rotor 18. Games 19 extend between the ferrule segments 5 and the vanes mobile 17, and we want them to be as small as possible in order to avoid an appreciable portion gases do not flow there. That’s why we designed many devices, not shown here but which are extensively described and the subject of many patents, to control the value of games 19 to everyone machine speeds: these are blowing of gas taken from another part of the machine to adjust the thermal expansions of the shell segments 5. But these precautions are somewhat little compromised by leaking gas slipping, through the intervals of the shell segments 5 and by the residual clearances between the flanges 4, the sails 10 and the sockets 15, in the empty volumes 20 internally delimited by the shell segments 5, externally by the casing 1 and axially by the flanges 4, the nuts of the bolts 7 and 12 and the seals 8. Air leaks tend to form a flow flow counterflow in the vein 14 and which excessively overheats casing 1, which expands it locally as well as the adjacent portions of ferrule segments 5.

Cet écoulement néfaste est interdit (figure 2) au moyen d'un corps d'étanchéité 25 composé essentiellement d'une bourre 26 contenue dans une enveloppe souple 27 et qui occupe la totalité ou presque de ces volumes vides 20 grâce à la souplesse du corps d'étanchéité 25 et à la compressibilité de la bourre 26, qui se déforment sous l'action des différences de pression environnantes et épousent les formes de la cavité 20. Les matériaux utilisés et notamment ceux de la bourre 26 sont mauvais conducteurs de la chaleur et peu perméables à l'air, tout en étant suffisamment poreux pour que la compressibilité de la bourre 26 ne soit pas compromise. La bourre 26 peut avoir une structure fibreuse, et l'enveloppe 27 être formée d'un tissu. This harmful flow is prohibited (figure 2) by means of a compound sealing body 25 essentially of a flock 26 contained in a flexible envelope 27 and which occupies all or almost of these empty volumes 20 thanks to the flexibility of the sealing body 25 and the compressibility of the wad 26, which deform under the action of surrounding pressure differences and espouse shapes of the cavity 20. The materials used and especially those of the flock 26 are bad conductors heat and not very breathable, while being sufficiently porous that the compressibility of the fill 26 is not compromised. Wad 26 can have a fibrous structure, and the envelope 27 be formed of a fabric.

La fibre peut être de la laine de quartz ou des feutres métalliques, et le tissu peut être un entrecroisement de fils de quartz, de verre, de carbone ou de métal.The fiber can be quartz wool or metallic felts, and the fabric can be a intertwining of quartz, glass, carbon wires or metal.

La figure 3 représente une conception un peu différente où le corps d'étanchéité, référencé alors 125 et encore constitué d'une bourre 26 contenue dans une enveloppe souple 27, est complété par un ressort 28 d'extension circulaire et dont la section et linéaire et forme un angle aigu, ou une épingle ouverte : il se compose de deux feuilles 29 sensiblement rigides qu'une charnière 30 élastique relie, et le volume 31 enclos par les feuilles 29 est vide. Le ressort 28 est comprimé, de sorte que les feuilles 29 tendent à s'écarter, ouvrant le ressort 28, et la bourre 26 est chassée vers l'extérieur et refoulée contre les surfaces du carter 1 et des segments de virole 5, y compris dans leurs anfractuosités.Figure 3 shows a design a little different where the sealing body, referenced then 125 and still consisting of a flock 26 contained in a flexible envelope 27, is completed by a spring 28 of circular extension and whose cross section and linear and forms an acute angle, or a pin open: it consists of two sheets 29 substantially rigid than an elastic hinge 30 connects, and the volume 31 enclosed by the sheets 29 is empty. The spring 28 is compressed, so that the sheets 29 tend to move apart, opening the spring 28, and the flock 26 is driven outwards and driven back against the surfaces of housing 1 and ferrule segments 5, including in their crevices.

La figure 4 représente le corps d'étanchéité 125 à l'état isolé. Il est fabriqué sous forme d'un boudin dont on coupe la longueur souhaitée et qu'on roule pour former un anneau dont les extrémités peuvent être obturées, ou même réunies entre elles par une couture, une soudure ou n'importe quel autre moyen approprié à l'enveloppe 27. Si les feuilles 29 sont élastiques et ont donc une certaine raideur, elles doivent cependant être suffisamment souples pour être courbées.Figure 4 shows the body seal 125 in an isolated state. It is manufactured under shape of a rod whose desired length is cut and that we roll to form a ring whose ends can be closed, or even joined between them by a seam, a weld or any other suitable means for envelope 27. If the sheets 29 are elastic and therefore have a certain stiffness, however, they should be flexible enough to be bent.

Un même mode de fabrication pourra être retenu pour la structure plus simple de la figure 1. Bien entendu, on pourra aussi utiliser un corps d'étanchéité composé de portions en blocs juxtaposés.The same manufacturing method could be retained for the simpler structure of FIG. 1. Of course, we can also use a body seal composed of portions in juxtaposed blocks.

Claims (3)

  1. Turbomachine wall comprising an outer casing (1), a shell ring surrounded by the casing and composed of segments (5) which are joined together and, by flanges (4), joined to the casing, and which, together with the casing and the flanges, delimit partitioned cavities (20), the said cavities being occupied by a sealing body (25, 125) formed of a flexible envelope (27) made of fabric and of a fibrous filling (26), in which wall the flexible envelope is not very permeable to air and deforms under the action of the various pressures around it so that it closely matches the shapes of the cavities (20).
  2. Turbomachine wall according to Claim 1, characterized in that the sealing body is also formed of a spring (28) contained in the flexible envelope and compressed to a smaller cross section than in the free state.
  3. Turbomachine wall according to Claim 2, characterized in that the spring in cross section has the shape of an opened-out hairpin.
EP19940402807 1993-12-08 1994-12-07 Turbine housing containing a sealing body Expired - Lifetime EP0657624B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9314699 1993-12-08
FR9314699A FR2713709B1 (en) 1993-12-08 1993-12-08 Turbomachine wall comprising a sealing body.

Publications (2)

Publication Number Publication Date
EP0657624A1 EP0657624A1 (en) 1995-06-14
EP0657624B1 true EP0657624B1 (en) 1998-02-04

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DE (1) DE69408423T2 (en)
FR (1) FR2713709B1 (en)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB9915637D0 (en) * 1999-07-06 1999-09-01 Rolls Royce Plc A rotor seal
GB0108398D0 (en) * 2001-04-04 2001-05-23 Siemens Ag Seal element for sealing a gap and combustion turbine having a seal element
FR2957115B1 (en) * 2010-03-05 2012-03-30 Snecma TURBINE STAGE IN A TURBOMACHINE
GB201103682D0 (en) * 2011-03-04 2011-04-20 Rolls Royce Plc A turbomachine casing assembly
EP2620653B1 (en) * 2012-01-25 2015-06-24 Rolls-Royce plc A turbomachine casing assembly with blade containment cavity
DE102013213834A1 (en) 2013-07-15 2015-02-19 MTU Aero Engines AG Method for producing an insulation element and insulation element for an aircraft engine housing
ES2718129T3 (en) 2013-07-23 2019-06-27 MTU Aero Engines AG Insulation device for a thermal gas turbine and a thermal gas turbine with this structure
US10337353B2 (en) * 2014-12-31 2019-07-02 General Electric Company Casing ring assembly with flowpath conduction cut
FR3086323B1 (en) * 2018-09-24 2020-12-11 Safran Aircraft Engines INTERNAL TURMOMACHINE HOUSING WITH IMPROVED THERMAL INSULATION

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1235694A (en) * 1958-07-28 1960-07-08 Connecticut Hard Rubber Co Seal structure resistant to high temperatures and fuels for jet engines and similar applications
FR2051912A5 (en) * 1969-07-01 1971-04-09 Rabouyt Denis
US4030288A (en) * 1975-11-10 1977-06-21 Caterpillar Tractor Co. Modular gas turbine engine assembly
DE2620762C2 (en) * 1976-05-11 1977-11-17 Motoren- und Turbinen-Union München GmbH, 8000 München Gap seal for turbo machines, in particular gas turbine jet engines
JPS61164003A (en) * 1985-01-11 1986-07-24 Hitachi Ltd Sealing device of stationary blade part generating thermal elongation in fluid machine
US5104286A (en) * 1991-02-08 1992-04-14 Westinghouse Electric Corp. Recirculation seal for a gas turbine exhaust diffuser

Also Published As

Publication number Publication date
DE69408423T2 (en) 1998-07-30
EP0657624A1 (en) 1995-06-14
FR2713709B1 (en) 1996-01-12
FR2713709A1 (en) 1995-06-16
DE69408423D1 (en) 1998-03-12

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