EP4165286B1 - Annular assembly for a turbomachine turbine - Google Patents

Annular assembly for a turbomachine turbine Download PDF

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Publication number
EP4165286B1
EP4165286B1 EP21737109.5A EP21737109A EP4165286B1 EP 4165286 B1 EP4165286 B1 EP 4165286B1 EP 21737109 A EP21737109 A EP 21737109A EP 4165286 B1 EP4165286 B1 EP 4165286B1
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EP
European Patent Office
Prior art keywords
circumferentially
crown
annular
sealing means
annular assembly
Prior art date
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EP21737109.5A
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German (de)
French (fr)
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EP4165286A1 (en
Inventor
Rémi-Paul Honoré GODIER
Etienne Gérard Joseph CANELLE
Alexandre CORSAUT
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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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
    • 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
    • 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
    • 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
    • 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
    • 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
    • F05D2240/55—Seals
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the distributor 2 comprises an external annular platform 6 fixed to a radial blade 8.
  • the row of moving blades 4 comprises an external annular platform 10 from which extend radially outwards lips 12 cooperating in sealing with an abradabe 14, for example of the honeycomb type belonging to a sectored ring carried by the casing 16 as is illustrated in the figure 1 .
  • This sealing member provides better aerothermal sealing between the thermal deflector sectors.
  • the sealing member makes it possible to thermally protect the casing by preventing leaks of hot gases from combustion at the circumferential junctions of the thermal deflector sectors.
  • the first sealing means may comprise a wall element applied from downstream to the circumferentially facing ends of two circumferentially consecutive deflector sectors.
  • the design of the first sealing means in the form of a wall element eliminates doubts about the presence of the sealing member during an endoscopy inspection. This design also eliminates any risk of forgetting to install the sealing members but also the risk of making a mistake in the direction of assembly.
  • the shape of these bodies thus provides coding when they are mounted between two ring sectors.
  • Each sealing member may comprise a first junction element connecting a first plate to the wall element, this first junction element being inserted circumferentially between two edges of circumferentially adjacent deflector sectors.
  • first and second junction elements make it possible to mechanically maintain the first sealing means to the second sealing means.
  • the second junction element can be arranged radially outside two edges of circumferentially adjacent deflector sectors.
  • the present document relates to a turbine for a turbomachine comprising a low pressure turbine comprising an annular assembly according to the aforementioned characteristics and a high pressure turbine, the external casing of the low pressure turbine comprising an upstream annular flange for fixing to a downstream annular flange of a external casing of the high pressure turbine.
  • This document concerns a turbomachine comprising an annular assembly of the aforementioned type.
  • a turbine includes an upstream high pressure turbine and a downstream low pressure turbine.
  • the high pressure turbine and the low pressure turbine each comprise alternating annular rows of stator blades and moving blades arranged inside a casing.
  • a first downstream moving blade wheel 4 is surrounded externally by a casing of the low pressure turbine 16a while an upstream outlet distributor 2 of the high pressure turbine is surrounded externally by a casing of the high pressure turbine 16b.
  • the distributor 2 comprises an external annular platform 6 to which the radially external ends of radial blades 8 are connected.
  • a hooking tab 32 is at one end of said external platform 6 of the distributor 2. The circumferential and axial retention of the distributor 2 is ensured via said tab hook 32 which is engaged in an annular groove 33 of the high pressure turbine casing 16b, this annular groove 33 opening downstream.
  • This casing of the high pressure turbine 16b is fixed at its downstream end by means of an annular flange 36 to an annular flange 38 of the upstream end of the low pressure turbine casing 16a.
  • the annular flanges 36, 38 are positioned radially at the level of the annular space separating the outlet distributor 2 of the high pressure turbine and the first movable wheel 4 of the low pressure turbine.
  • the first moving blade wheel 4 is rotatably mounted around a longitudinal axis X in a ring attached to the external casing 16a of the low pressure turbine.
  • the sectorized ring is formed of several ring sectors which are arranged circumferentially end to end and each carried by the external casing 16a of the low pressure turbine. The downstream ends of the ring sectors are clamped radially by a C-shaped clamping tab 22, located downstream of the ring sectors.
  • the deflector sector 20 has a general z shape and has a substantially curved orientation.
  • the deflector sector 20 comprises, from upstream to downstream, a wall sector extending radially towards the inside 40, an annular wall sector 42 and a wall sector extending radially towards the outside 44.
  • the sector wall extending radially outwards 44 is fixed by brazing to a downstream edge of a radial wall 46 of the crown sector 18.
  • the annular wall sector 42 of the deflector sector 20 circumferentially follows the direction of extension of the sector of crown 18.
  • the abradable 14 is of the honeycomb type and provides sealing at the level of the blade wheel 4 by means of annular lips 12 extending radially outwards from the external annular platform 10 of the movable wheel 4 , in order to limit the passage of air radially outside the movable wheel 4.
  • sealing tabs 52 are inserted at the level of longitudinal slots located in the longitudinal edges of the circumferential ends of the annular wall sector 48 of the crown sector 18.
  • the radial edges of the circumferential ends of the radial wall sector 46 of the crown sector 18 and the longitudinal edges of the circumferential ends of the cylindrical wall sector 48 of the crown sector 18 comprise slots 54, 55 for housing a member of waterproofing.
  • the sealing member 56 comprises first circumferential sealing means 58 between two circumferentially consecutive sectors of deflector 20, that is to say at the junction between two circumferentially consecutive sectors of deflector 20. It can also include second sealing means 60 between two circumferentially consecutive crown sectors 18.
  • the first sealing means 58 comprise a wall element 62 comprising a downstream radial wall 64 extending radially outwards and whose radially internal end is connected to an inclined wall 66 converging towards the axis of rotation going towards upstream, this inclined wall 66 being connected at its upstream end to an upstream radial wall 68 extending radially inwards.
  • This wall element 62 is shaped identically to the sectors of thermal deflectors 20 so as to be able to perfectly match the three-dimensional shape of two edges of sectors of deflectors 20 facing each other circumferentially.
  • the second sealing means 60 between two circumferentially consecutive crown sectors 18 comprise a first plate 70 and a second plate 72 which are disjointed. These first 70 and second 72 plates have a planar, substantially rectangular shape.
  • the first plate 70 is able to be inserted on a first side into a slot 54 of an edge of a circumferential end of a cylindrical wall sector 50 of a first crown sector 18 and on a second side , opposite the first side, in a slot 54 of one edge of a circumferential end of a cylindrical wall sector 50 of a second circumferentially consecutive crown sector 18.
  • the second plate 72 is able to be inserted on a first side into a slot 55 of a radial edge of a circumferential end of a radial wall sector 46 of a first crown sector 18 and of a second side, opposite the first side, in a slot 55 of a radial edge of one end circumferential of a radial wall sector of a second circumferentially consecutive crown sector 18.
  • the sealing member 56 comprises a first junction element 74 connecting the first plate 70 to the inclined wall 66 converging towards the axis of rotation going upstream of the wall element 62.
  • the first junction element 74 extends radially with a substantially frustoconical shape with a section flaring radially inwards. This first junction element 74 is fixed at its radially internal end to the wall element 62 and its radially external end to the internal face of the first plate 70.
  • the first junction element 74 extends radially and longitudinally.
  • the sealing member 56 also comprises a second junction element 76 connecting the second plate 72 to the downstream radial wall 64 extending radially towards the outside of the wall element 62.
  • the second junction element extends longitudinally with a substantially rectangular shape.
  • This second junction element 76 is fixed at its radially internal end to the wall element 62 and its radially external end to the internal face of the second plate 72.
  • the second junction element 76 can extend radially up to a third of a radial length of the second plate 72 from an internal end of the second plate 72.
  • the first junction element 70 and the second junction element 72 are flat and have a thickness of between 0.2 and 0.4 mm. This thickness is of the same order of magnitude as that of the first and second sealing means.
  • This sealing member 56 can be manufactured by additive manufacturing. Said sealing member 56 is mounted in circumferential translation, the radially outer face of said wall element 62 coming to match the shape of the downstream face of the thermal deflector sector 20, the first 70 and second 72 plates being inserted into said slots 54, 55 housing two sectors of circumferentially consecutive crowns 18.
  • the sealing member 56 makes it possible to prevent combustion gases from passing through the circumferential and radial clearances present between two sectors of circumferentially consecutive crowns 18 and between two sectors of consecutive deflectors 20.
  • the sealing member 56 makes it possible to block the air in the gap between the first 70 and the second 72 disjointed plate.
  • the joining of the second sealing means 60 with the first sealing means 58 makes it possible to facilitate the assembly of said sealing member 56.
  • the circumferential sealing between two crown sectors 18 is thus carried out simultaneously with the sealing between two circumferentially consecutive deflector setters 20, which avoids assembly oversights.
  • the design of the first sealing means 58 in the form of a wall element 62 removes doubts about the presence of the sealing member 56 during an endoscopy inspection.

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

Description

Domaine technique de l'inventionTechnical field of the invention

Le présent document concerne un organe d'étanchéité pour turbomachine, et plus particulièrement pour turbine basse pression.This document concerns a sealing member for a turbomachine, and more particularly for a low pressure turbine.

Etat de la technique antérieureState of the prior art

Classiquement, une turbomachine est constituée, d'amont en aval, d'un compresseur basse pression, d'un compresseur haute pression, d'une chambre de combustion, d'une turbine haute pression et d'une turbine basse pression. La turbine basse-pression permet d'exploiter et de libérer la puissance générée dans une chambre de combustion située en amont de ladite turbine basse pression. Deux flux d'air sont à considérer au sein d'une turbomachine : un flux annuliare primaire et un flux annulaire secondaire. Le flux secondaire contourne toute la partie chaude de la turbomachine. L'autre flux appelé flux primaire traverse toute la turbomachine du compresseur basse pression à la turbine basse pression et est entouré par le flux d'air secondaire. Ce flux primaire circule au sein d'une veine primaire.Conventionally, a turbomachine is made up, from upstream to downstream, of a low pressure compressor, a high pressure compressor, a combustion chamber, a high pressure turbine and a low pressure turbine. The low-pressure turbine makes it possible to exploit and release the power generated in a combustion chamber located upstream of said low-pressure turbine. Two air flows must be considered within a turbomachine: a primary annular flow and a secondary annular flow. The secondary flow bypasses the entire hot part of the turbomachine. The other flow called the primary flow passes through the entire turbomachine from the low pressure compressor to the low pressure turbine and is surrounded by the secondary air flow. This primary flow circulates within a primary vein.

Une turbine comprend une alternance de rangées annulaires d'aubes statoriques et d'aubes mobiles agencées à l'intérieur d'un carter. La figure 1 illustre une partie d'une telle turbine 1 et représente un distributeur 2 amont et une rangée annulaire d'aubes mobiles 4 aval.A turbine comprises alternating annular rows of stator blades and moving blades arranged inside a casing. There figure 1 illustrates a part of such a turbine 1 and represents an upstream distributor 2 and an annular row of moving blades 4 downstream.

Le distributeur 2 comporte une plateforme annulaire externe 6 fixée à une pale radiale 8. La rangée d'aubes mobiles 4 comporte une plateforme annulaire externe 10 depuis laquelle s'étendent radialement vers l'extérieur des léchettes 12 coopérant à étanchéité avec un abradabe 14, par exemple du type en nid d'abeille appartenant à un anneau sectorisé porté par le carter 16 comme cela est illustré sur la figure 1.The distributor 2 comprises an external annular platform 6 fixed to a radial blade 8. The row of moving blades 4 comprises an external annular platform 10 from which extend radially outwards lips 12 cooperating in sealing with an abradabe 14, for example of the honeycomb type belonging to a sectored ring carried by the casing 16 as is illustrated in the figure 1 .

L'anneau sectorisé circonférentiellement comprend une couronne 18 portant sur sa face radialement interne l'abradable 14. L'anneau comprend également un déflecteur thermique 20 porté par l'extrémité amont de la couronne 18. La couronne 18 est fixée au carter 16 de turbine par une patte de serrage 22 à forme en C solidiaire de l'extrémité amont d'une plateforme externe du distributeur agencé en aval de la roue mobile. L'extrémité amont de la couronne comprend un organe en C 24 pour la fixation de l'anneau sur un rail cylindrique 26 du carter 16 et sur un bras radial 28 du distributeur 2 amont. Le déflecteur 20 est fixé à un bord amont 30 de la couronne 18 et s'étend radialement vers l'intérieur.The circumferentially sectored ring comprises a crown 18 carrying on its radially internal face the abradable 14. The ring also comprises a thermal deflector 20 carried by the upstream end of the crown 18. The crown 18 is fixed to the turbine casing 16 by a C-shaped clamping tab 22 secured to the upstream end of an external platform of the distributor arranged downstream of the moving wheel. The upstream end of the crown comprises a C-shaped member 24 for fixing the ring on a cylindrical rail 26 of the casing 16 and on a radial arm 28 of the upstream distributor 2. The deflector 20 is fixed to an upstream edge 30 of the crown 18 and extends radially inwards.

Lorsque la turbomachine est en fonctionnement, les gaz de combustion passent d'amont en aval dans la veine primaire de la turbine et une partie de l'air chaud de combustion peut s'échapper entre l'extrémité aval de la plateforme externe 6 d'un distributeur 2 et l'extrémité amont de la plateforme externe 10 d'une roue mobile aval 4. Cet espace annulaire ainsi formé et noté J correspond à un espace nécessaire pour la rotation de roue mobile.When the turbomachine is in operation, the combustion gases pass from upstream to downstream in the primary stream of the turbine and part of the hot combustion air can escape between the downstream end of the external platform 6 of a distributor 2 and the end upstream of the external platform 10 of a downstream mobile wheel 4. This annular space thus formed and denoted J corresponds to a space necessary for the rotation of the mobile wheel.

Pour limiter le passage d'air chaud entre deux secteurs de couronnes 18, on a recours à des languettes engagées pour partie dans un secteur de couronne 18 et pour l'autre partie dans un secteur de couronne 18 circonférentiellement adjacent.To limit the passage of hot air between two sectors of crowns 18, use is made of tongues engaged partly in a sector of crown 18 and for the other part in a sector of crown 18 circumferentially adjacent.

Cependant de l'air peut toujours circuler entre deux secteurs de déflecteur 20 et venir endommager les fixations de l'anneau au carter, c'est-à-dire l'organe en C 24, le rail cylindrique 26 du carter 16, le bras radial 28 du déflecteur 20 amont et également le carter 16 lui-même. L'utilisation de languettes n'est pas envisageable puisque l'épaisseur du déflecteur est bien trop faible pour pouvoir envisager une telle solution.However, air can still circulate between two sectors of deflector 20 and damage the fixings of the ring to the casing, that is to say the C-shaped member 24, the cylindrical rail 26 of the casing 16, the arm radial 28 of the upstream deflector 20 and also the casing 16 itself. The use of tabs is not possible since the thickness of the deflector is far too small to be able to envisage such a solution.

Le présent document vise à remédier à ces inconvénients de manière fiable, efficace et peu onéreuse.This document aims to remedy these drawbacks in a reliable, efficient and inexpensive manner.

L'art antérieur pertinent est divulgué dans:

  • US 2005 / 002779 A1 : Segment de carénage destiné à être incorporé dans un moteur à turbine à gaz afin de supprimer l'influence des gaz de combustion chauds sur un carter de turbine du moteur à turbine à gaz. FR 3 083 563 A1 : Module d'étanchéité de turbine de turbomachine, en particulier d'aéronef, ce module d'étanchéité s'étendant autour d'un axe et comprenant un distributeur fixé à un carter.
  • CA 2 582 398 A1 : Dispositif de fixation de secteurs d'anneau sur un carter de turbine dans une turbomachine.
Relevant prior art is disclosed in:
  • US 2005 / 002779 A1 : Fairing segment intended to be incorporated into a gas turbine engine in order to eliminate the influence of hot combustion gases on a turbine casing of the gas turbine engine. FR 3 083 563 A1 : Turbine sealing module of a turbomachine, in particular of an aircraft, this sealing module extending around an axis and comprising a distributor fixed to a casing.
  • CA 2 582 398 A1 : Device for fixing ring sectors on a turbine casing in a turbomachine.

Présentation de l'inventionPresentation of the invention

Le présent document concerne un ensemble annulaire pour turbine de turbomachine, en particulier d'aéronef, ledit ensemble annulaire s'étendant le long d'une direction axiale X et comprenant :

  • un distributeur fixé à un carter externe;
  • une roue à aubes agencée en aval du distributeur et montée rotative à l'intérieur du carter externe ;
  • ladite roue à aubes étant entourée par un anneau sectorisé circonférentiellement et porté par le carter externe et formé d'une couronne agencée radialement à l'extérieur de la roue à aubes et d'un déflecteur annulaire porté par un bord amont de la couronne et s'étendant radialement vers l'intérieur depuis ledit bord amont de la couronne caractérisé en ce qu'il comprend des organes d'étanchéité entre deux secteurs d'anneau circonférentiellemment adjancents, ces organes d'étanchéité comprenant des premiers moyens d'étanchéité circonférentiels entre deux secteurs de déflecteur circonférentiellement consécutifs.
This document relates to an annular assembly for a turbomachine turbine, in particular an aircraft turbine, said annular assembly extending along an axial direction X and comprising:
  • a distributor attached to an external casing;
  • a paddle wheel arranged downstream of the distributor and rotatably mounted inside the outer casing;
  • said impeller being surrounded by a ring sectored circumferentially and carried by the external casing and formed of a crown arranged radially outside the impeller and of an annular deflector carried by an upstream edge of the crown and s extending radially inwards from said upstream edge of the crown characterized in that it comprises sealing members between two circumferentially adjacent ring sectors, these sealing members comprising first circumferential sealing means between two circumferentially consecutive deflector sectors.

Cet organe d'étanchéité confère une meilleure étanchéité aérothermique entre les secteurs de déflecteurs thermiques. L'organe d'étanchéité permet de protéger thermiquement le carter en évitant les fuites de gaz chauds issus de la combustion au niveau des jonctions circonférentielles des secteurs de déflecteurs thermiques.This sealing member provides better aerothermal sealing between the thermal deflector sectors. The sealing member makes it possible to thermally protect the casing by preventing leaks of hot gases from combustion at the circumferential junctions of the thermal deflector sectors.

Les premiers moyens d'étanchéité circonférentiels peuvent être agencés à la jonction entre deux secteurs de déflecteur circonférentiellement consécutifs.The first circumferential sealing means can be arranged at the junction between two circumferentially consecutive deflector sectors.

Les organes d'étanchéité peuvent comprendre des seconds moyens d'étanchéité circonférentiels entre deux secteurs de couronne circonférentiellement consécutifs, ces seconds moyens d'étanchiété étant solidaires des premiers moyens d'étanchéité.The sealing members may comprise second sealing means circumferential between two circumferentially consecutive crown sectors, these second sealing means being integral with the first sealing means.

Les second moyens d'étanchéité permettent d'éviter les fuites de gaz de combustion entre deux secteurs de couronne circonférentiellement consécutifs. La solidarisation des seconds moyens d'étanchéité avec les premiers moyens d'étanchéité permet de faciliter l'assemblage dudit organe d'étanchéité. L'étanchéité circonférentielle entre deux secteurs de couronne est ainsi réalisée de manière simultanée à l'étanchéité entre deux seteurs de déflecteur circonférentiellement consécutif ce qui évite des oublis de montage.The second sealing means make it possible to prevent combustion gas leaks between two circumferentially consecutive crown sectors. The joining of the second sealing means with the first sealing means makes it possible to facilitate the assembly of said sealing member. The circumferential sealing between two crown sectors is thus carried out simultaneously with the sealing between two circumferentially consecutive deflector setters, which avoids mounting oversights.

Les premiers moyens d'étanchéité peuvent comprendre un élément de paroi appliqué depuis l'aval sur les extrémités en vis-à-vis circonférentiel de deux secteurs de déflecteur circonférentiellement consécutifs.The first sealing means may comprise a wall element applied from downstream to the circumferentially facing ends of two circumferentially consecutive deflector sectors.

La conception des premiers moyens d'étanchéité sous forme d'un élément de paroi supprime les doutes sur la présence de l'organe d'étanchéité lors d'une inspection par endoscopie. Cette conception supprime également tout risque d'oubli au montage des organes d'étanchéité mais aussi le risque de se tromper dans le sens de montage. La forme de ces organes réalise ainsi un détrompage à leur montage entre deux secteurs d'anneau.The design of the first sealing means in the form of a wall element eliminates doubts about the presence of the sealing member during an endoscopy inspection. This design also eliminates any risk of forgetting to install the sealing members but also the risk of making a mistake in the direction of assembly. The shape of these bodies thus provides coding when they are mounted between two ring sectors.

Les seconds moyens d'étanchéité peuvent comprendre au moins une première plaquette et une seconde plaquette disjointes et reliées l'une et l'autre aux premiers moyens d'étanchéité, la première plaquette et la seconde plaquette étant engagées dans une fente d'un bord d'un premier secteur de couronne et pour une autre partie dans une fente d'un bord en vis-à-vis circonférentiel d'un second secteur de couronne circonférentiellement adjacent.The second sealing means may comprise at least a first plate and a second plate disjointed and both connected to the first sealing means, the first plate and the second plate being engaged in a slot of one edge of a first crown sector and for another part in a slot of a circumferentially facing edge of a second circumferentially adjacent crown sector.

On comprend que la solidarisation des plaquettes aux premiers moyens évite tout oubli de montage de l'une ou l'autre des plaquettes puisque celles-ci sont montées entre deux secteurs d'anneau simultanément aux premiers moyens.It is understood that the securing of the plates to the first means avoids any forgetting to mount one or the other of the plates since they are mounted between two ring sectors simultaneously with the first means.

Chaque organe d'étanchéité peut comprendre un premier élément de jonction reliant une première plaquette à l'élément de paroi, ce premier élément de jonction étant intercalé circonférentiellement entre deux bords de secteurs de déflecteurs circonférentiellement adjacents.Each sealing member may comprise a first junction element connecting a first plate to the wall element, this first junction element being inserted circumferentially between two edges of circumferentially adjacent deflector sectors.

Chaque organe d'étanchéité peut comprendre un second élément de jonction reliant une seconde plaquette à l'élément de paroi, ce second élément de jonction étant intercalé circonférentiellement entre deux bords de secteurs de couronne circonférentiellement adjacents.Each sealing member may comprise a second junction element connecting a second plate to the wall element, this second junction element being inserted circumferentially between two edges of circumferentially adjacent crown sectors.

Ces premier et second élément de jonction permettent de conférer de la robustesse, de la solidité audit organe d'étanchéité. Ces premier et second éléments de jonction permettent de faciliter la direction de montage dudit organe d'étanchéité.These first and second joining elements make it possible to provide robustness and solidity to said sealing member. These first and second junction elements make it possible to facilitate the direction of assembly of said sealing member.

Ces premier et second éléments de jonction permettent de maintenir mécaniquement les premiers moyens d'étanchéité aux seconds moyens d'étanchéité.These first and second junction elements make it possible to mechanically maintain the first sealing means to the second sealing means.

Le second élément de jonction peut être agencé radialement à l'extérieur de deux bords de secteurs de déflecteurs circonférentiellement adjacents.The second junction element can be arranged radially outside two edges of circumferentially adjacent deflector sectors.

Le présent document concerne une turbine pour turbomachine comprenant une turbine basse pression comportant un ensemble annulaire selon les caractéristiques précitées et une turbine haute pression, le carter externe de la turbine basse pression comprenant une bride annulaire amont de fixation à une bride annulaire aval d'un carter externe de la turbine haute pression. Le présent document concerne une turbomachine comprenant un ensemble annulaire du type précité.The present document relates to a turbine for a turbomachine comprising a low pressure turbine comprising an annular assembly according to the aforementioned characteristics and a high pressure turbine, the external casing of the low pressure turbine comprising an upstream annular flange for fixing to a downstream annular flange of a external casing of the high pressure turbine. This document concerns a turbomachine comprising an annular assembly of the aforementioned type.

Brève description des figuresBrief description of the figures

  • [Fig. 1] représente une demie-vue schématique partielle en coupe axiale d'un module de turbomachine ;[ Fig. 1 ] represents a partial schematic half-view in axial section of a turbomachine module;
  • [Fig. 2] représente une demie-vue schématique partielle en coupe axiale d'un module de turbomachine selon l'invention ;[ Fig. 2 ] represents a partial schematic half-view in axial section of a turbomachine module according to the invention;
  • [Fig. 3] représente une vue schématique en perspective d'un secteur d'anneau d'étanchéité du module de la figure 2, selon l'invention ;[ Fig. 3 ] represents a schematic perspective view of a sealing ring sector of the module of the figure 2 , according to the invention;
  • [Fig. 4] représente une vue schématique en perspective de deux secteurs d'anneau circonférentiellement consécutifs et d'un organe d'étanchéité, selon l'invention ;[ Fig. 4 ] represents a schematic perspective view of two circumferentially consecutive ring sectors and a sealing member, according to the invention;
  • [Fig. 5] représente une vue schématique en perspective d'un organe d'étanchéité monté dans un secteur d'anneau vu de côté, selon l'invention ;[ Fig. 5 ] represents a schematic perspective view of a sealing member mounted in a ring sector seen from the side, according to the invention;
  • [Fig. 6] représente une vue schématique en perspective d'un organe d'étanchéité monté dans un secteur d'anneau vu depuis l'aval, selon l'invention ;[ Fig. 6 ] represents a schematic perspective view of a sealing member mounted in a ring sector seen from downstream, according to the invention;
  • [Fig. 7] représente une vue schématique en perspective d'un organe d'étanchéité brut de fusion, selon l'invention.[ Fig. 7 ] represents a schematic perspective view of an as-molded sealing member, according to the invention.
Description détaillée de l'inventionDetailed description of the invention

Une turbine comprend une turbine haute pression amont et une turbine basse pression aval. La turbine haute pression et la turbine basse pression comprennent chacune une alternance de rangées annulaires d'aubes statoriques et d'aubes mobiles agencées à l'intérieur d'un carter. Comme illustré sur la figure 2, une première roue d'aubes mobiles aval 4 est entourée extérieurement par un carter de la turbine basse pression 16a alors qu'un distributeur de sortie amont 2 de la turbine haute pression est entouré extérieurement par un carter de la turbine haute pression 16b. Le distributeur 2 comporte une plateforme annulaire externe 6 à laquelle sont reliées les exrémités radialement externes de pales radiales 8. Une patte d'accrochage 32 est à une extrémité de ladite plateforme externe 6 du distributeur 2. Le maintien circonférentiel et axial du distributeur 2 est assuré par l'intermédiaire de ladite patte d'accrochage 32 qui est engagée dans une gorge annulaire 33 du carter de turbine haute pression 16b, cette gorge annulaire 33 débouchant vers l'aval.A turbine includes an upstream high pressure turbine and a downstream low pressure turbine. The high pressure turbine and the low pressure turbine each comprise alternating annular rows of stator blades and moving blades arranged inside a casing. As illustrated on the figure 2 , a first downstream moving blade wheel 4 is surrounded externally by a casing of the low pressure turbine 16a while an upstream outlet distributor 2 of the high pressure turbine is surrounded externally by a casing of the high pressure turbine 16b. The distributor 2 comprises an external annular platform 6 to which the radially external ends of radial blades 8 are connected. A hooking tab 32 is at one end of said external platform 6 of the distributor 2. The circumferential and axial retention of the distributor 2 is ensured via said tab hook 32 which is engaged in an annular groove 33 of the high pressure turbine casing 16b, this annular groove 33 opening downstream.

Ce carter de la turbine haute pression 16b est fixé à son extrémité aval au moyen d'une bride annulaire 36 à une bride annulaire 38 de l'extrémité amont du carter de turbine basse pression 16a. Les brides annulaires 36, 38 sont positionnées radialement au niveau de l'espace annulaire séparant le distributeur de sortie 2 de la turbine haute pression et la première roue mobile 4 de la turbine basse pression.This casing of the high pressure turbine 16b is fixed at its downstream end by means of an annular flange 36 to an annular flange 38 of the upstream end of the low pressure turbine casing 16a. The annular flanges 36, 38 are positioned radially at the level of the annular space separating the outlet distributor 2 of the high pressure turbine and the first movable wheel 4 of the low pressure turbine.

Comme illustré à la figure 2, la première roue d'aubes mobiles 4 est montée rotative autour d'un axe longitudinal X dans un anneau accroché au carter externe 16a de la turbine basse pression. L'anneau sectorisé est formé de plusieurs secteurs d'anneau qui sont agencés circonférentiellement bout à bout et chacun porté par le carter externe 16a de la turbine basse pression. Les extrémités aval des secteurs d'anneau sont serrés radialement par une patte de serrage 22 en forme de C, situé en aval des secteurs d'anneau.As illustrated in figure 2 , the first moving blade wheel 4 is rotatably mounted around a longitudinal axis X in a ring attached to the external casing 16a of the low pressure turbine. The sectorized ring is formed of several ring sectors which are arranged circumferentially end to end and each carried by the external casing 16a of the low pressure turbine. The downstream ends of the ring sectors are clamped radially by a C-shaped clamping tab 22, located downstream of the ring sectors.

Comme illustré aux figures 3 à 6, chaque secteur d'anneau comprend un secteur de couronne 18 agencé radialement à l'extérieur de la roue à aubes 4 et un secteur de déflecteur 20 thermique annulaire.As illustrated in figures 3 to 6 , each ring sector comprises a crown sector 18 arranged radially outside the blade wheel 4 and an annular thermal deflector sector 20.

Le secteur de déflecteur 20 a une forme générale en z et a une orientation sensiblement incurvée. Le secteur de déflecteur 20 comporte, d'amont en aval, un secteur de paroi s'étendant radialement vers l'intérieur 40, un secteur de paroi annulaire 42 et un secteur de paroi s'étendant radialement vers l'extérieur 44. Le secteur de paroi s'étendant radialement vers l'extérieur 44 est fixépar brasure sur un bord aval d'une paroi radiale 46 du secteur de couronne 18. Le secteur de paroi annulaire 42 du secteur de déflecteur 20 circonférentiellement suit la direction d'extension du secteur de couronne 18. Le secteur de déflecteur 20 a une étendue circonférentielle sensiblement identique à celle du secteur de couronne 18 et à l'abradable 14 de sorte que les extrémités circonférentielles du secteur de déflecteur 20 soient sensiblement alignées axialement avec celles du secteur de couronne 18 et de l'abradable 14. Ce secteur de déflecteur 20 peut être un secteur de tôle annulaire. Comme illustré aux figures 2 à 6, le secteur de couronne 18 s'étend circonférentiellement et comprend un secteur de paroi annulaire 48 dont la face interne porte un abradable 14, un secteur de paroi radial 46 s'étendant radialement vers l'intérieur relié à un secteur de paroi cylindrique 50 engagé dans une gorge annulaire 34 portée par la bride annulaire 38 de l'extrémité amont du carter de turbine basse pression 16a. L'abradable 14 est de type nid d'abeille et réalise l'étanchéité au niveau de la roue d'aubes 4 au moyen de léchettes annulaires 12 s'étendant radialement vers l'extérieur depuis la plateforme annulaire externe 10 de la roue mobile 4, afin de limiter le passage d'air radialement à l'extérieur de la roue mobile 4. Classiquement, comme illustré en figure 4, des languettes d'étanchéité 52 sont insérées au niveau de fentes longitudinales situées dans les bords longitudinaux des extrémités circonférentielles du secteur de paroi annulaire 48 du secteur de couronne 18. Ces languettes d'étanchéité 52 sont insérées chacune, d'un premier côté dans une fente d'un bord longitudinal d'une extrémité circonférentielle d'un secteur de paroi annulaire 48 d'un premier secteur de couronne 18 et d'un deuxième côté de ladite languette d'étanchéité 52, dans une fente d'un bord longitudinal d'une extrémité circonférentielle d'un secteur de paroi annulaire 48 d'un second secteur de couronne 18 circonférentiellement consécutif. Ces languettes d'étanchéité 52 ont une forme générale plane et allongée.The deflector sector 20 has a general z shape and has a substantially curved orientation. The deflector sector 20 comprises, from upstream to downstream, a wall sector extending radially towards the inside 40, an annular wall sector 42 and a wall sector extending radially towards the outside 44. The sector wall extending radially outwards 44 is fixed by brazing to a downstream edge of a radial wall 46 of the crown sector 18. The annular wall sector 42 of the deflector sector 20 circumferentially follows the direction of extension of the sector of crown 18. The deflector sector 20 has a circumferential extent substantially identical to that of the crown sector 18 and to the abradable 14 so that the circumferential ends of the deflector sector 20 are substantially aligned axially with those of the crown sector 18 and the abradable 14. This sector of deflector 20 can be a sector of annular sheet metal. As illustrated in figures 2 to 6 , the crown sector 18 extends circumferentially and comprises an annular wall sector 48 whose internal face carries an abradable 14, a radial wall sector 46 extending radially inwards connected to an engaged cylindrical wall sector 50 in an annular groove 34 carried by the annular flange 38 of the upstream end of the low pressure turbine casing 16a. The abradable 14 is of the honeycomb type and provides sealing at the level of the blade wheel 4 by means of annular lips 12 extending radially outwards from the external annular platform 10 of the movable wheel 4 , in order to limit the passage of air radially outside the movable wheel 4. Conventionally, as illustrated in Figure 4 , sealing tabs 52 are inserted at the level of longitudinal slots located in the longitudinal edges of the circumferential ends of the annular wall sector 48 of the crown sector 18. These sealing tabs 52 are each inserted, on a first side in a slot of a longitudinal edge of a circumferential end of an annular wall sector 48 of a first crown sector 18 and a second side of said sealing tab 52, in a slot of a longitudinal edge of a circumferential end of an annular wall sector 48 of a second crown sector 18 circumferentially consecutive. These sealing tabs 52 have a generally flat and elongated shape.

Comme illustré en figure 3, des bords radiaux des extrémités circonférentielles du secteur de paroi radial 46 du secteur de couronne 18 et des bords longitudinaux des extrémités circonférentielles du secteur de paroi cylindrique 48 du secteur de couronne 18 comportent des fentes 54, 55 de logement d'un organe d'étanchéité.As illustrated in Figure 3 , the radial edges of the circumferential ends of the radial wall sector 46 of the crown sector 18 and the longitudinal edges of the circumferential ends of the cylindrical wall sector 48 of the crown sector 18 comprise slots 54, 55 for housing a member of waterproofing.

Comme illustré sur les figures 4 à 7, l'organe d'étanchéité 56 comprend des premiers moyens d'étanchéité 58 circonférentiels entre deux secteurs de déflecteur 20 circonférentiellement consécutifs, c'est-à-dire à la jonction entre deux secteurs de déflecteur 20 circonférentiellement consécutifs. Il peut aussi comprendre des seconds moyens d'étanchéité 60 entre deux secteurs de couronne 18 circonférentiellement consécutifs.As illustrated on the figures 4 to 7 , the sealing member 56 comprises first circumferential sealing means 58 between two circumferentially consecutive sectors of deflector 20, that is to say at the junction between two circumferentially consecutive sectors of deflector 20. It can also include second sealing means 60 between two circumferentially consecutive crown sectors 18.

Les premiers moyens d'étanchéité 58comprennent un élément de paroi 62 comportant une paroi radiale aval 64 s'étendant radialement vers l'extérieur et dont l'extrémité radialement interne est reliée à une paroi inclinée 66 convergeant vers l'axe de rotation en allant vers l'amont, cette paroi inclinée 66 étant reliée à son extrémité amont à une paroi radiale amont 68 s'étendant radialement vers l'intérieur.The first sealing means 58 comprise a wall element 62 comprising a downstream radial wall 64 extending radially outwards and whose radially internal end is connected to an inclined wall 66 converging towards the axis of rotation going towards upstream, this inclined wall 66 being connected at its upstream end to an upstream radial wall 68 extending radially inwards.

Cet élément de paroi 62 est conformé de manière identique aux secteurs de déflecteurs 20 thermique de manière à pouvoir épouser parfaitement la forme tridimensionnelle de deux bords de secteurs de déflecteurs 20 en vis-à-vis circonférentiels.This wall element 62 is shaped identically to the sectors of thermal deflectors 20 so as to be able to perfectly match the three-dimensional shape of two edges of sectors of deflectors 20 facing each other circumferentially.

Les seconds moyens d'étanchéité 60 entre deux secteurs de couronne 18 circonférentiellement consécutifs comprennent une première plaquette 70 et une seconde plaquette 72 disjointes. Ces première 70 et seconde 72 plaquettes ont une forme plane, sensiblement rectangulaire. La première plaquette 70 est apte à s'insérer d'un premier côté dans une fente 54 d'un bord d'une extrémité circonférentielle d'un secteur de paroi cylindrique 50 d'un premier secteur de couronne 18 et d'un second côté, opposé au premier côté, dans une fente 54 d'un bord d'une extrémité circonférentielle d'un secteur de paroi cylindrique 50 d'un second secteur de couronne 18 circonférentiellement consécutif. La seconde plaquette 72 est apte à s'insérer d'un premier côté dans une fente 55 d'un bord radial d'une extrémité circonférentielle d'un secteur de paroi radial 46 d'un premier secteur de couronne 18 et d'un second côté, opposé au premier côté, dans une fente 55 d'un bord radial d'une extrémité circonférentielle d'un secteur de paroi radial d'un second secteur de couronne 18 circonférentiellement consécutif.The second sealing means 60 between two circumferentially consecutive crown sectors 18 comprise a first plate 70 and a second plate 72 which are disjointed. These first 70 and second 72 plates have a planar, substantially rectangular shape. The first plate 70 is able to be inserted on a first side into a slot 54 of an edge of a circumferential end of a cylindrical wall sector 50 of a first crown sector 18 and on a second side , opposite the first side, in a slot 54 of one edge of a circumferential end of a cylindrical wall sector 50 of a second circumferentially consecutive crown sector 18. The second plate 72 is able to be inserted on a first side into a slot 55 of a radial edge of a circumferential end of a radial wall sector 46 of a first crown sector 18 and of a second side, opposite the first side, in a slot 55 of a radial edge of one end circumferential of a radial wall sector of a second circumferentially consecutive crown sector 18.

L'organe d'étanchéité 56 comporte un premier élément de jonction 74 reliant la première plaquette 70 à la paroi inclinée 66 convergeant vers l'axe de rotation en allant vers l'amont de l'élement de paroi 62. Le premier élément de jonction 74 s'étend radialement avec une forme sensiblement tronconique à section s'évasant radialement vers l'intérieur. Ce premier élément de jonction 74 est fixé à son extrémité radialement interne à l'élément de paroi 62 et son extrémité radialement externe à la face interne de la première plaquette 70. Le premier élément de jonction 74 s'étend radialement et longitudinalement.The sealing member 56 comprises a first junction element 74 connecting the first plate 70 to the inclined wall 66 converging towards the axis of rotation going upstream of the wall element 62. The first junction element 74 extends radially with a substantially frustoconical shape with a section flaring radially inwards. This first junction element 74 is fixed at its radially internal end to the wall element 62 and its radially external end to the internal face of the first plate 70. The first junction element 74 extends radially and longitudinally.

L'organe d'étanchéité 56 comprend également un second élément de jonction 76 reliant la seconde plaquette 72 à la paroi radiale aval 64 s'étendant radialement vers l'extérieur de l'élément de paroi 62. Le second élément de jonction s'étend longitudinalement avec une forme sensiblement rectangulaire. Ce second élément de jonction 76 est fixé à son extrémité radialement interne à l'élément de paroi 62 et son extrémité radialement externe à la face interne de la seconde plaquette 72. Le second élément de jonction 76 peut s'étendre radialement jusqu'au tiers d'une longueur radiale de la seconde plaquette 72 depuis une extrémité interne de la seconde plaquette 72.The sealing member 56 also comprises a second junction element 76 connecting the second plate 72 to the downstream radial wall 64 extending radially towards the outside of the wall element 62. The second junction element extends longitudinally with a substantially rectangular shape. This second junction element 76 is fixed at its radially internal end to the wall element 62 and its radially external end to the internal face of the second plate 72. The second junction element 76 can extend radially up to a third of a radial length of the second plate 72 from an internal end of the second plate 72.

Le premier élément de jonction 70 et le second élément de jonction 72 sont planes et d'épaisseur comprise entre 0.2 et 0.4 mm. Cet épaisseur est du même ordre de grandeur que celle des premiers et second moyens d'étanchéité.The first junction element 70 and the second junction element 72 are flat and have a thickness of between 0.2 and 0.4 mm. This thickness is of the same order of magnitude as that of the first and second sealing means.

Cet organe d'étanchéité 56 peut être fabriqué par fabrication additive. Ledit organe d'étanchéité 56 est monté en translation circonférentielle, la face radialement extérieure dudit élément de paroi 62 venant épouser la forme de la face aval du secteur de déflecteur 20 thermique, les première 70 et seconde 72 plaquettes venant s'insérer dans lesdites fentes 54, 55 de logements de deux secteurs de couronnes 18 circonférentiellement consécutifs.This sealing member 56 can be manufactured by additive manufacturing. Said sealing member 56 is mounted in circumferential translation, the radially outer face of said wall element 62 coming to match the shape of the downstream face of the thermal deflector sector 20, the first 70 and second 72 plates being inserted into said slots 54, 55 housing two sectors of circumferentially consecutive crowns 18.

Le présent document est particulièrement intéressant dans le contexte où il est utilisé, i.e. à la jonction entre le carter haute pression 16b et basse pression 16a pusisque cette zone de jonction de carters peut être plus sensible qu'une autre à des fuites d'air chaud, les éléments de fixation pouvant être affectés et les dilatations thermiques différentielles entre les deux carters pouvant conduire à une augmentation de contrainte dans ceux-ci au niveau de leur fixation.This document is particularly interesting in the context in which it is used, i.e. at the junction between the high pressure casing 16b and low pressure casing 16a since this casing junction zone can be more sensitive than another to hot air leaks , the fixing elements may be affected and the differential thermal expansions between the two casings may lead to an increase in stress in them at the level of their fixing.

L'organe d'étanchéité 56 permet d'éviter que des gaz de combustion ne passent à travers les jeux circonférentiels et radiaux présents entre deux secteurs de couronnes 18 circonférentiellement consécutifs et entre deux secteurs de déflecteurs 20 consécutifs. L'organe d'étanchéité 56 permet de bloquer l'air dans l'interstice entre la première 70 et la seconde 72 plaquette disjointes.The sealing member 56 makes it possible to prevent combustion gases from passing through the circumferential and radial clearances present between two sectors of circumferentially consecutive crowns 18 and between two sectors of consecutive deflectors 20. The sealing member 56 makes it possible to block the air in the gap between the first 70 and the second 72 disjointed plate.

La solidarisation des seconds moyens d'étanchéité 60 avec les premiers moyens d'étanchéité 58 permet de faciliter l'assemblage dudit organe d'étanchéité 56. L'étanchéité circonférentielle entre deux secteurs de couronne 18 est ainsi réalisée de manière simultanée à l'étanchéité entre deux seteurs de déflecteur 20 circonférentiellement consécutif ce qui évite des oublis de montage.The joining of the second sealing means 60 with the first sealing means 58 makes it possible to facilitate the assembly of said sealing member 56. The circumferential sealing between two crown sectors 18 is thus carried out simultaneously with the sealing between two circumferentially consecutive deflector setters 20, which avoids assembly oversights.

La conception des premiers moyens d'étanchéité 58 sous forme d'un élément de paroi 62 supprime les doutes sur la présence de l'organe d'étanchéité 56 lors d'une inspection par endoscopie.The design of the first sealing means 58 in the form of a wall element 62 removes doubts about the presence of the sealing member 56 during an endoscopy inspection.

Claims (8)

  1. Annular assembly for a turbomachine turbine, in particular of an aircraft, said annular assembly extending about a longitudinal axis X and comprising:
    - a distributor (2) fixed to an external casing (16);
    - a bladed disc (4) arranged downstream of the distributor (2) and mounted so as to rotate inside the external casing (16);
    - said bladed disc (4) being surrounded by a circumferentially segmented ring and supported by the external casing (16) and formed by a crown (18) arranged radially to the exterior of the bladed disc (4) and an annular deflector (20) supported by an upstream edge of the crown (18) and extending radially towards the interior from said upstream edge of the crown (18);
    sealing members (56) between two circumferentially adjacent ring segments, these sealing members (56) comprising first circumferential sealing means (58) arranged at the junction between two circumferentially consecutive deflector segments (20) and
    characterized in that the sealing members (56) comprise second circumferential sealing means (60) between two circumferentially consecutive crown segments (18), these second sealing means (60) being connected to the first sealing means (58).
  2. Annular assembly according to claim 1, wherein the first sealing means (58) comprise a wall element (62) applied from downstream to the ends circumferentially opposite two circumferentially consecutive deflector segments (20).
  3. Annular assembly according to claims 1 or 2, wherein the second sealing means (60) comprise at least one first plate (70) and one second plate (72) which are disconnected and connected to the first sealing means (58), the first plate (70) and the second plate (72) being engaged in a slot (54, 55) of an edge of a first crown segment (18) and for another part into a slot (54, 55) of an edge circumferentially facing a second circumferentially adjacent crown segment (18).
  4. Annular assembly according to claim 3, wherein each sealing member (56) comprises a first connecting element (74) connecting a first plate (70) to the wall element (62), this first connecting element (74) being interposed circumferentially between two edges of circumferentially adjacent deflector segments (20).
  5. Annular assembly according to claim 3 or 4, wherein each sealing member (56) comprises a second connecting element (76) connecting a second plate (72) to the wall element (62), this second connecting element (76) being interposed circumferentially between two edges of circumferentially adjacent crown segments (18).
  6. Annular assembly according to claim 5, wherein said second connecting element (76) is arranged radially outside of two edges of circumferentially adjacent deflector segments (20).
  7. Turbomachine turbine comprising a low-pressure turbine including an annular assembly according to any of the preceding claims and a high-pressure turbine, the external casing of the low-pressure turbine comprising an upstream annular flange (36) for attachment to a downstream annular flange (38) of an external casing of the high-pressure turbine.
  8. Turbomachine comprising an annular assembly according to any of claims 1 to 6.
EP21737109.5A 2020-06-11 2021-06-10 Annular assembly for a turbomachine turbine Active EP4165286B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2006131A FR3111382B1 (en) 2020-06-11 2020-06-11 Annular assembly for turbomachine turbine
PCT/FR2021/051043 WO2021250357A1 (en) 2020-06-11 2021-06-10 Annular assembly for a turbomachine turbine

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EP4165286A1 EP4165286A1 (en) 2023-04-19
EP4165286B1 true EP4165286B1 (en) 2024-05-22

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US (1) US12018576B2 (en)
EP (1) EP4165286B1 (en)
CN (1) CN115917120A (en)
FR (1) FR3111382B1 (en)
WO (1) WO2021250357A1 (en)

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FR3140112A1 (en) * 2022-09-22 2024-03-29 Safran Aircraft Engines Improvement of sealing in a turbomachine turbine

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5188507A (en) * 1991-11-27 1993-02-23 General Electric Company Low-pressure turbine shroud
US7186078B2 (en) * 2003-07-04 2007-03-06 Ishikawajima-Harima Heavy Industries Co., Ltd. Turbine shroud segment
FR2899275A1 (en) * 2006-03-30 2007-10-05 Snecma Sa Ring sector fixing device for e.g. turboprop of aircraft, has cylindrical rims engaged on casing rail, where each cylindrical rim comprises annular collar axially clamped on casing rail using annular locking unit
EP2964934B1 (en) * 2013-03-08 2018-10-03 United Technologies Corporation Gas turbine engine component having variable width feather seal slot
US20180347399A1 (en) * 2017-06-01 2018-12-06 Pratt & Whitney Canada Corp. Turbine shroud with integrated heat shield
FR3071273B1 (en) * 2017-09-21 2019-08-30 Safran Aircraft Engines TURBINE SEALING ASSEMBLY FOR TURBOMACHINE
FR3083563B1 (en) 2018-07-03 2020-07-24 Safran Aircraft Engines AIRCRAFT TURBOMACHINE SEALING MODULE

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FR3111382A1 (en) 2021-12-17
WO2021250357A1 (en) 2021-12-16
US20230340893A1 (en) 2023-10-26
FR3111382B1 (en) 2022-12-23
CN115917120A (en) 2023-04-04
EP4165286A1 (en) 2023-04-19
US12018576B2 (en) 2024-06-25

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