EP0356305B1 - Turbine stator ring held by a turbine casing - Google Patents

Turbine stator ring held by a turbine casing Download PDF

Info

Publication number
EP0356305B1
EP0356305B1 EP89402256A EP89402256A EP0356305B1 EP 0356305 B1 EP0356305 B1 EP 0356305B1 EP 89402256 A EP89402256 A EP 89402256A EP 89402256 A EP89402256 A EP 89402256A EP 0356305 B1 EP0356305 B1 EP 0356305B1
Authority
EP
European Patent Office
Prior art keywords
turbine
segment
ring
stator
casing
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP89402256A
Other languages
German (de)
French (fr)
Other versions
EP0356305A1 (en
Inventor
François Emile Georges Crozet
Jean Luc Soupizon
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
Priority date (The priority date 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 date listed.)
Filing date
Publication date
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 EP0356305A1 publication Critical patent/EP0356305A1/en
Application granted granted Critical
Publication of EP0356305B1 publication Critical patent/EP0356305B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments

Definitions

  • the present invention relates to a turbine stator, in particular for a low-pressure turbine of a turbofan engine, comprising a stator ring associated with a support for connection to the turbine casing.
  • FR-A-2 407 342 and FR-A-2 407 343 thus illustrate an example of such an assembly in which the support of a turbine ring is constituted, on its upstream edge, by a segmented ferrule fixed by fasteners on an external envelope and, on its downstream edge, by a radial flange of said envelope and a flange of the neighboring distributor stage.
  • US-A-3 603 599 describes a turbine sealing ring secured by means of a hook mounting to an annular support fixed by bolts to a turbine casing, studs being arranged between the ring and the support.
  • US-A-4,648,792 describes a turbine stator blade support assembly further comprising a sealing ring facing a stage of movable blades made up of segments whose downstream edge is supported by the external platform stator vanes and the upstream edge is connected by a support to a radial ring secured to the turbine casing.
  • FIG. 1 also represents a known example of embodiment of the front part, seen in longitudinal section of the low pressure turbine of a known turbofan engine.
  • a turbine ring 2 is mounted on an annular support 3 which is bolted to the upstream flange 4 of the turbine casing 5.
  • a layer 6 of insulating material can be interposed between the ring 2 and its support 3.
  • the invention aims to improve the thermal insulation of the casing and of the ring support itself while reducing the mass, which is a particularly important selection criterion for aeronautical applications.
  • One of the aims is also to make the ring support independent of the turbine casing.
  • a turbine stator comprising a stator ring associated with a support for connection to the turbine casing, said ring consisting of a sheet metal ferrule formed of a plurality of sectors each comprising two segments, a first segment, generally oriented in a longitudinal direction relative to the turbine, bearing an abradable type seal and a second segment, generally oriented in a radial direction relative to the turbine, secured by its radially internal end with one end of said first segment and cooperating by its radially external end with said ring support which has an S-shaped section and whose radially outer groove cooperates with an annular hook characterized in that said hook is part of the turbine casing, the downstream edge of the first segment is supported on a spoiler of the blades of the distributor stage neighbor and the radially internal end is secured to the upstream end of said first segment.
  • a turbine stator ring 10 is constituted by a plurality of sectors, for example eighteen in number in the example shown.
  • Each sector comprises two sheet metal shell segments, a first segment 10a generally oriented in a longitudinal direction relative to the turbine and a second segment 10b, generally oriented in a radial direction and whose radially internal end 10c is secured, for example by welding, with the upstream end 10d of the first segment 10a.
  • the first segments 10a carry, on their internal face and in line with the ends of the movable blades 11 of the first turbine rotor stage, a seal 12 of abradable type.
  • the downstream edge 10e of the first segments 10a bears on the upstream spoilers 13a of the fixed vanes 13 of the turbine distributor.
  • the turbine casing 14 carries at its upstream end an annular hook 14a which cooperates with the radially outer groove 15a of a ring support 15 which has an S-shaped section.
  • This support 15 is of annular shape comprising a slot which gives said audit support 15 freedom of thermal expansion.
  • the end radially external of the second segments 10b has a flange 10f which cooperates with the radially inner groove 15b of the support 15. The turbine ring 10 is thus suspended between the support 15 and the spoilers of blades 13.
  • Between the turbine casing 14 and the turbine ring 10 is provided with a space allowing to have on the external face of the first segments 10a a first layer 16 of thermally insulating material which is covered with a sheet in the shape of a ferrule 17, itself carrying a second layer 18 of thermally insulating material.
  • the front part of the turbine comprising the stator ring according to the invention can be mounted in the manner described below.
  • the ring support 15 is mounted on the turbine casing 14; the second layer 18 of thermal insulator is placed in the casing; the covering ring 17 is positioned then the first layer 16 of thermal insulation is put in place.
  • the downstream edge 10e of the turbine ring sectors 10 is then tilted towards the axis of the turbojet engine and then said sectors are engaged on the upstream side in the internal groove 15b of the support 15 and moved axially until they press at the bottom of the groove 15b of the support 15 and the downstream edge 10e is tilted outwards.
  • Said downstream edge 10e of the first segments 10a further carries an anti-rotation lug 19 which is then used to position them angularly, said lugs 19 being held by a tool.
  • the first movable stage 11 of the rotor is then mounted, then the distributor 13 which comprises, on the upstream side of the external ring, a housing 20 cooperating with the pins 19 by which the turbine ring 10 is thus prevented from rotating.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

La présente invention concerne un stator de turbine, notamment pour une turbine basse-pression d'un turboréacteur à double flux, comprenant un anneau de stator associé à un support de liaison au carter de turbine.The present invention relates to a turbine stator, in particular for a low-pressure turbine of a turbofan engine, comprising a stator ring associated with a support for connection to the turbine casing.

Dans une turbine, et c'est notamment le cas pour une turbine destinée à des applications aéronautiques plus particulièrement visées par la présente invention, il est habituel d'interposer entre les extrémités des aubes du rotor de turbine et le carter de turbine proprement dit qui forme l'enveloppe et le support des éléments de stator, notamment des aubes fixes, une pièce fixe de forme générale annulaire qui porte une garniture d'étanchéité de type abradable, au droit des extrémités des aubes mobiles, et qui sera dénommée anneau de turbine.In a turbine, and this is particularly the case for a turbine intended for aeronautical applications more particularly targeted by the present invention, it is usual to interpose between the ends of the blades of the turbine rotor and the turbine casing itself which forms the casing and the support of the stator elements, in particular fixed blades, a fixed part of generally annular shape which carries a seal of abradable type, in line with the ends of the movable blades, and which will be called turbine ring .

Divers moyens ont été proposés pour le montage dudit anneau de turbine sur le carter. FR-A-2 407 342 et FR-A-2 407 343 illustrent ainsi un exemple d'un tel montage dans lequel le support d'un anneau de turbine est constitué, sur son bord amont, par une virole segmentée fixée par des attaches sur une enveloppe externe et, sur son bord aval, par une bride radiale de ladite enveloppe et un rebord de l'étage distributeur voisin.Various means have been proposed for mounting said turbine ring on the casing. FR-A-2 407 342 and FR-A-2 407 343 thus illustrate an example of such an assembly in which the support of a turbine ring is constituted, on its upstream edge, by a segmented ferrule fixed by fasteners on an external envelope and, on its downstream edge, by a radial flange of said envelope and a flange of the neighboring distributor stage.

US-A-3 603 599 décrit un anneau d'étanchéité de turbine solidarisé au moyen d'un montage à crochet à un support annulaire fixé par boulons à un carter de turbine, des goujons étant disposés entre l'anneau et le support.US-A-3 603 599 describes a turbine sealing ring secured by means of a hook mounting to an annular support fixed by bolts to a turbine casing, studs being arranged between the ring and the support.

US-A-4 648 792 décrit un ensemble de support d'aube de stator de turbine comportant en outre un anneau d'étanchéité au regard d'un étage d'aubes mobiles constitué de segments dont le bord aval est supporté par la plateforme externe des aubes de stator et le bord amont est relié par un support à un anneau radial solidaire du carter de turbine.US-A-4,648,792 describes a turbine stator blade support assembly further comprising a sealing ring facing a stage of movable blades made up of segments whose downstream edge is supported by the external platform stator vanes and the upstream edge is connected by a support to a radial ring secured to the turbine casing.

La figure 1 représente également un exemple connu de réalisation de la partie avant, vue en coupe longitudinale de la turbine basse pression d'un turboréacteur connu à double flux. Au niveau du premier étage 1 du rotor de turbine, un anneau de turbine 2 est monté sur un support annulaire 3 qui est boulonné sur la bride amont 4 du carter 5 de turbine. Une couche 6 de matériau isolant peut être interposée entre l'anneau 2 et son support 3.FIG. 1 also represents a known example of embodiment of the front part, seen in longitudinal section of the low pressure turbine of a known turbofan engine. At the first stage 1 of the turbine rotor, a turbine ring 2 is mounted on an annular support 3 which is bolted to the upstream flange 4 of the turbine casing 5. A layer 6 of insulating material can be interposed between the ring 2 and its support 3.

L'invention vise à améliorer l'isolation thermique du carter et du support d'anneau lui-même tout en réduisant la masse qui est un critère de choix particulièrement important pour les applications aéronautiques. Un des buts recherchés est également de rendre le support d'anneau indépendant du carter de turbine.The invention aims to improve the thermal insulation of the casing and of the ring support itself while reducing the mass, which is a particularly important selection criterion for aeronautical applications. One of the aims is also to make the ring support independent of the turbine casing.

Ces problèmes sont résolus par un stator de turbine comprenant un anneau de stator associé à un support de liaison au carter de turbine, ledit anneau étant constitué d'une virole en tôle formée d'une pluralité de secteurs comprenant chacun deux segments, un premier segment , orienté généralement suivant une direction longitudinale par rapport à la turbine, portant une garniture d'étanchéité de type abradable et un second segment , orienté généralement suivant une direction radiale par rapport à la turbine, solidarisé par son extrémité radialement interne avec une extrémité dudit premier segment et coopérant par son extrémité radialement externe avec ledit support d'anneau qui présente une section en S et dont la gorge radialement extérieure coopère avec un crochet annulaire caractérisé en ce que ledit crochet fait partie du carter de turbine, le bord aval du premier segment est en appui sur un becquet des aubes de l'étage de distributeur voisin et l'extrémité radialement interne est solidarisée avec l'extrémité amont dudit premier segment.These problems are solved by a turbine stator comprising a stator ring associated with a support for connection to the turbine casing, said ring consisting of a sheet metal ferrule formed of a plurality of sectors each comprising two segments, a first segment, generally oriented in a longitudinal direction relative to the turbine, bearing an abradable type seal and a second segment, generally oriented in a radial direction relative to the turbine, secured by its radially internal end with one end of said first segment and cooperating by its radially external end with said ring support which has an S-shaped section and whose radially outer groove cooperates with an annular hook characterized in that said hook is part of the turbine casing, the downstream edge of the first segment is supported on a spoiler of the blades of the distributor stage neighbor and the radially internal end is secured to the upstream end of said first segment.

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 de l'invention, en référence aux dessins annexés sur lesquels :

  • la figure 1 précédemment décrite en détails représente une vue en coupe longitudinale par un plan passant par l'axe de rotation de la turbine d'une partie avant d'une turbine basse pression d'un turboréacteur à double flux.
    d'un type connu, montrant une réalisation antérieure connue d'un anneau de stator de turbine monté sur un carter de turbine ;
  • la figure 2 représente, selon une vue en coupe analogue à celle de la figure 1, un anneau de stator suivant un mode de réalisation conforme à l'invention monté sur une turbine.
Other characteristics and advantages of the invention will be better understood on reading the following description of an embodiment of the invention, with reference to the appended drawings in which:
  • Figure 1 previously described in detail shows a longitudinal sectional view through a plane passing through the axis of rotation of the turbine of a front part of a low pressure turbine of a turbofan engine.
    of a known type, showing a known prior embodiment of a turbine stator ring mounted on a turbine housing;
  • 2 shows, in a sectional view similar to that of Figure 1, a stator ring according to an embodiment according to the invention mounted on a turbine.

Un anneau 10 de stator de turbine, selon un mode de réalisation de l'invention et tel que représenté sur la figure 2, est constitué par une pluralité de secteurs, par exemple au nombre de dix-huit dans l'exemple représenté. Chaque secteur comprend deux segments de virole en tôle, un premier segment 10a orienté généralement selon une direction longitudinale par rapport à la turbine et un second segment 10b, orienté généralement selon une direction radiale et dont l'extrémité radialement interne 10c est solidarisée, par exemple par soudure, avec l'extrémité amont 10d du premier segment 10a. Les premiers segments 10a portent, sur leur face interne et au droit des extrémités des aubes mobiles 11 du premier étage de rotor de turbine, une garniture 12 d'étanchéité de type abradable. Le bord aval 10e des premiers segments 10a est en appui sur les becquets amont 13a des aubes fixes 13 de distributeur de turbine. Le carter de turbine 14 porte à son extrémité amont un crochet annulaire 14a qui coopère avec la gorge radialement extérieure 15a d'un support d'anneau 15 qui présente une section en S. Ce support 15 est de forme annulaire comportant une fente qui confère audit support 15 une liberté de dilatation thermique. L'extrémité radialement externe des seconds segments 10b présente un rebord 10f qui coopère avec la gorge radialement intérieure 15b du support 15. L'anneau de turbine 10 se trouve ainsi suspendu entre le support 15 et les becquets d'aubes 13. Entre le carter de turbine 14 et l'anneau de turbine 10 se trouve ménagé un espace permettant de disposer sur la face externe des premiers segments 10a une première couche 16 de matériau thermiquement isolant qui est recouverte d'une tôle en forme de virole 17, portant elle-même une seconde couche 18 de matériau thermiquement isolant.A turbine stator ring 10, according to an embodiment of the invention and as shown in FIG. 2, is constituted by a plurality of sectors, for example eighteen in number in the example shown. Each sector comprises two sheet metal shell segments, a first segment 10a generally oriented in a longitudinal direction relative to the turbine and a second segment 10b, generally oriented in a radial direction and whose radially internal end 10c is secured, for example by welding, with the upstream end 10d of the first segment 10a. The first segments 10a carry, on their internal face and in line with the ends of the movable blades 11 of the first turbine rotor stage, a seal 12 of abradable type. The downstream edge 10e of the first segments 10a bears on the upstream spoilers 13a of the fixed vanes 13 of the turbine distributor. The turbine casing 14 carries at its upstream end an annular hook 14a which cooperates with the radially outer groove 15a of a ring support 15 which has an S-shaped section. This support 15 is of annular shape comprising a slot which gives said audit support 15 freedom of thermal expansion. The end radially external of the second segments 10b has a flange 10f which cooperates with the radially inner groove 15b of the support 15. The turbine ring 10 is thus suspended between the support 15 and the spoilers of blades 13. Between the turbine casing 14 and the turbine ring 10 is provided with a space allowing to have on the external face of the first segments 10a a first layer 16 of thermally insulating material which is covered with a sheet in the shape of a ferrule 17, itself carrying a second layer 18 of thermally insulating material.

La partie avant de la turbine comportant l'anneau de stator conforme à l'invention peut être montée de la manière ci-après décrite. Le support 15 d'anneau est monté sur le carter de turbine 14 ; la seconde couche 18 d'isolant thermique est mise en place dans le carter ; la virole 17 de recouvrement est positionnée puis la première couche 16 d'isolant thermique est mise en place. Successivement, le bord aval 10e des secteurs d'anneau de turbine 10 est alors basculé vers l'axe du turboréacteur puis lesdits secteurs sont engagés du côté amont dans la gorge intérieure 15b du support 15 et déplacés axialement jusqu'à les appuyer au fond de la gorge 15b du support 15 et le bord aval 10e est rebasculé vers l'extérieur. Ledit bord aval 10e des premiers segments 10a porte en outre un tenon antirotation 19 qui est alors utilisé pour les positionner angulairement, lesdits tenons 19 étant maintenus par un outillage. Le premier étage mobile 11 de rotor est alors monté puis le distributeur 13 qui comporte du côté amont de l'anneau externe un logement 20 coopérant avec les tenons 19 par lesquels l'anneau de turbine 10 est ainsi bloqué en rotation.The front part of the turbine comprising the stator ring according to the invention can be mounted in the manner described below. The ring support 15 is mounted on the turbine casing 14; the second layer 18 of thermal insulator is placed in the casing; the covering ring 17 is positioned then the first layer 16 of thermal insulation is put in place. Successively, the downstream edge 10e of the turbine ring sectors 10 is then tilted towards the axis of the turbojet engine and then said sectors are engaged on the upstream side in the internal groove 15b of the support 15 and moved axially until they press at the bottom of the groove 15b of the support 15 and the downstream edge 10e is tilted outwards. Said downstream edge 10e of the first segments 10a further carries an anti-rotation lug 19 which is then used to position them angularly, said lugs 19 being held by a tool. The first movable stage 11 of the rotor is then mounted, then the distributor 13 which comprises, on the upstream side of the external ring, a housing 20 cooperating with the pins 19 by which the turbine ring 10 is thus prevented from rotating.

Claims (3)

  1. Turbine stator comprising a stator ring associated with a support (15) connecting it to the casing of the turbine, the said ring (10) being made up of shell in sheet metal formed by a plurality of sectors each comprising two segments, a first segment (10a), generally oriented in a longitudinal direction relative to the turbine, carrying a sealing lining (12) of the abradable type and a second segment (10b), generally oriented in a radial direction relative to the turbine, fixed at its radially inner end (10c) to one end (10d) of the said first segment (10a) and working in conjunction at its radially outer end (10f) with the said ring support (15) which has an S-shaped profile and of which the radially outer throat (15a) works in conjunction with an annular hook (14a), characterised in that the said hook is part of the turbine casing (14), the downstream edge (10e) of the first segment bears against a nib (13a) on the blades (13) of the adjoining distributor stage and the radially inner end is fixed to the upstream end of the said first segment.
  2. Turbine stator in accordance with Claim 1 characterised in that the outer face of the first segment (10a) is covered by a first layer (16) of thermally insulating material which supports a cover sheet in the form of a shell (17), itself covered with a second layer (18) of thermally insulating material.
  3. Turbine stator in accordance with either of Claims 1 and 2 characterised in that each ring sector (10a and 10b) carries on its downstream edge (10e) an anti-rotation tenon (19) working in conjunction with a housing (20) formed in the upstream edge of the adjoining turbine distributor(13).
EP89402256A 1988-08-18 1989-08-10 Turbine stator ring held by a turbine casing Expired - Lifetime EP0356305B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8810977A FR2635562B1 (en) 1988-08-18 1988-08-18 TURBINE STATOR RING ASSOCIATED WITH A TURBINE HOUSING BINDING SUPPORT
FR8810977 1988-08-18

Publications (2)

Publication Number Publication Date
EP0356305A1 EP0356305A1 (en) 1990-02-28
EP0356305B1 true EP0356305B1 (en) 1994-01-12

Family

ID=9369384

Family Applications (1)

Application Number Title Priority Date Filing Date
EP89402256A Expired - Lifetime EP0356305B1 (en) 1988-08-18 1989-08-10 Turbine stator ring held by a turbine casing

Country Status (5)

Country Link
US (1) US4925365A (en)
EP (1) EP0356305B1 (en)
JP (1) JPH0694801B2 (en)
DE (1) DE68912241T2 (en)
FR (1) FR2635562B1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3935273B1 (en) * 2019-03-08 2023-01-18 Safran Aircraft Engines Counter rotating gas turbine for an aircraft

Families Citing this family (56)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2226365B (en) * 1988-12-22 1993-03-10 Rolls Royce Plc Turbomachine clearance control
US5197281A (en) * 1990-04-03 1993-03-30 General Electric Company Interstage seal arrangement for airfoil stages of turbine engine counterrotating rotors
IE67360B1 (en) * 1990-09-25 1996-03-20 United Technologies Corp Apparatus and method for a stator assembly of a rotary machine
US5228195A (en) * 1990-09-25 1993-07-20 United Technologies Corporation Apparatus and method for a stator assembly of a rotary machine
US5188507A (en) * 1991-11-27 1993-02-23 General Electric Company Low-pressure turbine shroud
US5201846A (en) * 1991-11-29 1993-04-13 General Electric Company Low-pressure turbine heat shield
DE4331060C1 (en) * 1993-09-13 1994-06-30 Gruenzweig & Hartmann Montage Heat insulation arrangement for thermic turbo-machines with hollow spaces
EP0844369B1 (en) * 1996-11-23 2002-01-30 ROLLS-ROYCE plc A bladed rotor and surround assembly
US6120242A (en) * 1998-11-13 2000-09-19 General Electric Company Blade containing turbine shroud
FR2786222B1 (en) * 1998-11-19 2000-12-29 Snecma LAMELLE SEALING DEVICE
EP1045115A1 (en) * 1999-04-12 2000-10-18 Asea Brown Boveri AG Heat shield for a gas turbine
JP2002129901A (en) * 2000-10-30 2002-05-09 Ishikawajima Harima Heavy Ind Co Ltd Chip shroud structure
DE10122464C1 (en) * 2001-05-09 2002-03-07 Mtu Aero Engines Gmbh Mantle ring for low pressure turbine stage of gas turbine uses segments each having seal carrier and relatively spaced security element with minimum contact between them
FR2829176B1 (en) * 2001-08-30 2005-06-24 Snecma Moteurs STATOR CASING OF TURBOMACHINE
US6814541B2 (en) * 2002-10-07 2004-11-09 General Electric Company Jet aircraft fan case containment design
US20060267289A1 (en) * 2003-06-20 2006-11-30 Elliott Company Hybrid abradable labyrinth damper seal
GB2407343B (en) * 2003-10-22 2006-04-19 Rolls Royce Plc An acoustic liner for a gas turbine engine casing
FR2867224B1 (en) * 2004-03-04 2006-05-19 Snecma Moteurs AXIAL AXIS HOLDING DEVICE FOR RING OF A TURBOMACHINE HIGH-PRESSURE TURBINE
DE102005011742A1 (en) * 2005-03-11 2006-09-14 Johnson Controls Gmbh Foam part for a vehicle, in particular for a seat and in particular with sensor means
FR2899273B1 (en) * 2006-03-30 2012-08-17 Snecma DEVICE FOR FASTENING RING SECTIONS ON A TURBINE HOUSING OF A TURBOMACHINE
US7665960B2 (en) 2006-08-10 2010-02-23 United Technologies Corporation Turbine shroud thermal distortion control
FR2923525B1 (en) * 2007-11-13 2009-12-18 Snecma SEALING A ROTOR RING IN A TURBINE FLOOR
US8429816B2 (en) * 2008-09-12 2013-04-30 General Electric Company Stator ring configuration
JP2010216321A (en) * 2009-03-16 2010-09-30 Hitachi Ltd Moving blade of steam turbine, and steam turbine using the same
FR2952965B1 (en) * 2009-11-25 2012-03-09 Snecma INSULATING A CIRCONFERENTIAL SIDE OF AN EXTERNAL TURBOMACHINE CASTER WITH RESPECT TO A CORRESPONDING RING SECTOR
US8939715B2 (en) * 2010-03-22 2015-01-27 General Electric Company Active tip clearance control for shrouded gas turbine blades and related method
FR2960591B1 (en) * 2010-06-01 2012-08-24 Snecma DEVICE FOR ROTATING A DISPENSING SEGMENT IN A TURBOMACHINE HOUSING; PION ANTIROTATION
US9080459B2 (en) * 2012-01-03 2015-07-14 General Electric Company Forward step honeycomb seal for turbine shroud
FR2989724B1 (en) * 2012-04-20 2015-12-25 Snecma TURBINE STAGE FOR A TURBOMACHINE
EP2696036A1 (en) * 2012-08-09 2014-02-12 MTU Aero Engines GmbH Clamping ring for a turbomachine
EP2696037B1 (en) 2012-08-09 2017-03-01 MTU Aero Engines AG Sealing of the flow channel of a fluid flow engine
EP2719869A1 (en) * 2012-10-12 2014-04-16 MTU Aero Engines GmbH Axial sealing in a housing structure for a turbomachine
EP2725203B1 (en) * 2012-10-23 2019-04-03 MTU Aero Engines AG Cool air guide in a housing structure of a fluid flow engine
US9803491B2 (en) * 2012-12-31 2017-10-31 United Technologies Corporation Blade outer air seal having shiplap structure
DE102013205883B4 (en) * 2013-04-03 2020-04-23 MTU Aero Engines AG Arrangement of guide vane segments and method for producing such an arrangement
US20160040547A1 (en) * 2013-04-12 2016-02-11 United Technologies Corporation Blade outer air seal with secondary air sealing
RU2534669C1 (en) * 2013-11-25 2014-12-10 Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) Low-pressure turbine stator
WO2015084550A1 (en) * 2013-12-03 2015-06-11 United Technologies Corporation Heat shields for air seals
JP6233578B2 (en) * 2013-12-05 2017-11-22 株式会社Ihi Turbine
US10253645B2 (en) 2013-12-12 2019-04-09 United Technologies Corporation Blade outer air seal with secondary air sealing
US10145308B2 (en) * 2014-02-10 2018-12-04 United Technologies Corporation Gas turbine engine ring seal
FR3025124B1 (en) * 2014-08-28 2016-09-30 Snecma PROCESS FOR MANUFACTURING TURBOMACHINE ORGAN RING BRACKETS
EP3153671A1 (en) 2015-10-08 2017-04-12 MTU Aero Engines GmbH Protection device for a turbomachine
EP3179053B1 (en) 2015-12-07 2019-04-03 MTU Aero Engines GmbH Casing structure of a turbomachine with heat protection shield
FR3058755B1 (en) * 2016-11-15 2020-09-25 Safran Aircraft Engines TURBINE FOR TURBOMACHINE
DE102016222720A1 (en) * 2016-11-18 2018-05-24 MTU Aero Engines AG Sealing system for an axial flow machine and axial flow machine
FR3065483B1 (en) * 2017-04-24 2020-08-07 Safran Aircraft Engines SEALING DEVICE BETWEEN ROTOR AND TURBOMACHINE STATOR
US20180347399A1 (en) * 2017-06-01 2018-12-06 Pratt & Whitney Canada Corp. Turbine shroud with integrated heat shield
EP3412871B1 (en) 2017-06-09 2021-04-28 Ge Avio S.r.l. Sealing arrangement for a turbine vane assembly
JP7061497B2 (en) * 2018-03-30 2022-04-28 三菱重工航空エンジン株式会社 Aircraft gas turbine
DE102018210598A1 (en) 2018-06-28 2020-01-02 MTU Aero Engines AG Housing structure for a turbomachine, turbomachine and method for cooling a housing section of a housing structure of a turbomachine
DE102018210600A1 (en) * 2018-06-28 2020-01-02 MTU Aero Engines AG COAT RING ARRANGEMENT FOR A FLOWING MACHINE
FR3086323B1 (en) * 2018-09-24 2020-12-11 Safran Aircraft Engines INTERNAL TURMOMACHINE HOUSING WITH IMPROVED THERMAL INSULATION
JP2021110291A (en) * 2020-01-10 2021-08-02 三菱重工業株式会社 Rotor blade and axial flow rotary machine
CA3182646A1 (en) * 2021-12-24 2023-06-24 Itp Next Generation Turbines, S.L. A turbine arrangement including a turbine outlet stator vane arrangement
US11933226B2 (en) * 2022-05-13 2024-03-19 Rtx Corporation Heat shield and method of installing the same

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB839915A (en) * 1958-01-20 1960-06-29 Rolls Royce Labyrinth seals
US3603599A (en) * 1970-05-06 1971-09-07 Gen Motors Corp Cooled seal
US3880550A (en) * 1974-02-22 1975-04-29 Us Air Force Outer seal for first stage turbine
US3966354A (en) * 1974-12-19 1976-06-29 General Electric Company Thermal actuated valve for clearance control
US4053254A (en) * 1976-03-26 1977-10-11 United Technologies Corporation Turbine case cooling system
DE2745130C2 (en) * 1977-10-07 1980-01-03 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Sealing device for the free blade ends of axial turbines
US4157232A (en) * 1977-10-31 1979-06-05 General Electric Company Turbine shroud support
US4177004A (en) * 1977-10-31 1979-12-04 General Electric Company Combined turbine shroud and vane support structure
US4213296A (en) * 1977-12-21 1980-07-22 United Technologies Corporation Seal clearance control system for a gas turbine
US4257222A (en) * 1977-12-21 1981-03-24 United Technologies Corporation Seal clearance control system for a gas turbine
US4242042A (en) * 1978-05-16 1980-12-30 United Technologies Corporation Temperature control of engine case for clearance control
FR2452601A1 (en) * 1979-03-30 1980-10-24 Snecma REMOVABLE SEALING COVER FOR TURBOJET BLOWER HOUSING
GB2081392B (en) * 1980-08-06 1983-09-21 Rolls Royce Turbomachine seal
GB2081817B (en) * 1980-08-08 1984-02-15 Rolls Royce Turbine blade shrouding
GB2115487B (en) * 1982-02-19 1986-02-05 Gen Electric Double wall compressor casing
FR2552159B1 (en) * 1983-09-21 1987-07-10 Snecma DEVICE FOR CONNECTING AND SEALING TURBINE STATOR BLADE SECTIONS
GB2151709B (en) * 1983-12-19 1988-07-27 Gen Electric Improvements in gas turbine engines
JPS6157441A (en) * 1984-08-30 1986-03-24 Nippon Seiki Co Ltd Warning indicator system
US4648792A (en) * 1985-04-30 1987-03-10 United Technologies Corporation Stator vane support assembly

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3935273B1 (en) * 2019-03-08 2023-01-18 Safran Aircraft Engines Counter rotating gas turbine for an aircraft

Also Published As

Publication number Publication date
DE68912241D1 (en) 1994-02-24
DE68912241T2 (en) 1994-05-11
JPH0694801B2 (en) 1994-11-24
FR2635562A1 (en) 1990-02-23
EP0356305A1 (en) 1990-02-28
US4925365A (en) 1990-05-15
FR2635562B1 (en) 1993-12-24
JPH02104903A (en) 1990-04-17

Similar Documents

Publication Publication Date Title
EP0356305B1 (en) Turbine stator ring held by a turbine casing
CA2622116C (en) High-pressure turbine of a turbomachine
CA2569564C (en) Improved turbine engine distributor
CA2647057C (en) Sectorized distributor for a turbine
EP1265031B1 (en) Fixing of metallic cowls on turbomachine combustion chamber liners made of CMC materials
EP2504529B1 (en) Insulation of a circumferential edge of an outer casing of a turbine engine from a corresponding ring sector
FR3084103A1 (en) SEALING ASSEMBLY FOR A TURBOMACHINE TURBINE ROTOR AND TURBOMACHINE TURBINE COMPRISING SUCH AN ASSEMBLY
EP3421730B1 (en) Turbine for turbine engine with sealing ring comprising two parts
FR3058756A1 (en) TURBINE FOR TURBOMACHINE
FR2971022A1 (en) COMPRESSOR RECTIFIER STAGE FOR A TURBOMACHINE
EP1517006A1 (en) Gas turbine brush seal arrangement for cabin air supply
EP3880939B1 (en) Sealing between a rotor and a vane of a turbomachine
FR3071273B1 (en) TURBINE SEALING ASSEMBLY FOR TURBOMACHINE
FR3061741A1 (en) TURBINE FOR TURBOMACHINE
EP4208626B1 (en) Turbine of a turbomachine comprising wear liners for thermal protection
FR3079553A1 (en) ASSEMBLY FOR TURBOMACHINE
FR2961556A1 (en) Turbine i.e. low pressure turbine, for e.g. turbojet engine of airplane, has axial and radial support units that are not in contact with casing to avoid heating, by conduction, of casing by sectorized ring during operation
FR2944554A1 (en) High pressure turbine for turbo machine of aircraft, has downstream radial wall carrying axial support unit supported on upstream radial wall for axially retaining external structure of distributor with respect to case
FR3069276B1 (en) SEALING ASSEMBLY FOR TURBOMACHINE
FR3121168A1 (en) Reduction of leaks in a turbomachine
FR3139856A1 (en) TURBOMACHINE WHEEL
WO2023247903A1 (en) Bladed assembly for a turbomachine, turbine for a turbomachine, and turbomachine
FR3061511A1 (en) TURBINE FOR TURBOMACHINE
FR3094028A1 (en) TURBINE INCLUDING A RIVETED SEALING RING
FR3065484A1 (en) TURBOMACHINE TURBINE ASSEMBLY

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 19890911

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB

17Q First examination report despatched

Effective date: 19910325

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 19940118

REF Corresponds to:

Ref document number: 68912241

Country of ref document: DE

Date of ref document: 19940224

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

REG Reference to a national code

Ref country code: FR

Ref legal event code: TP

Ref country code: FR

Ref legal event code: CD

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20070816

Year of fee payment: 19

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20070731

Year of fee payment: 19

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20070725

Year of fee payment: 19

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20080810

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20090430

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20080901

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20090303

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20080810