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EP2513428A1 - Turbine stage of a turbine engine - Google Patents

Turbine stage of a turbine engine

Info

Publication number
EP2513428A1
EP2513428A1 EP10809013A EP10809013A EP2513428A1 EP 2513428 A1 EP2513428 A1 EP 2513428A1 EP 10809013 A EP10809013 A EP 10809013A EP 10809013 A EP10809013 A EP 10809013A EP 2513428 A1 EP2513428 A1 EP 2513428A1
Authority
EP
European Patent Office
Prior art keywords
ring
annular
downstream
casing
turbine stage
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.)
Withdrawn
Application number
EP10809013A
Other languages
German (de)
French (fr)
Inventor
Emmanuel Berche
Vincent Philippot
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
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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP2513428A1 publication Critical patent/EP2513428A1/en
Withdrawn legal-status Critical Current

Links

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
    • 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
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to a turbine stage in a turbomachine such as a turbojet engine or a turboprop engine.
  • a turbomachine essentially comprises, from upstream to downstream, a compressor, a combustion chamber and a turbine, the compressor supplying the combustion chamber with pressurized air, and the turbine receiving the hot gases coming from the combustion chamber to extract them from the combustion chamber. 'energy.
  • a low-pressure turbine stage comprises a rectifier formed of an annular row of stationary vanes extending radially between two inner and outer annular platforms and a rotor wheel mounted downstream of the rectifier inside. a sectorized ring carried by a casing surrounding the turbine stage.
  • Each ring sector carries on an inner face a seal cooperating with the outer peripheries of the vanes of the rotor wheel and comprises on an outer face of the attachment means on the housing formed by upstream and downstream circumferential rims.
  • the upstream circumferential flange is engaged axially in an annular groove carried by an upstream annular tab of the casing and the downstream circumferential flange is clamped radially on an annular tab downstream of the casing by a C-section locking member axially engaged from downstream on the circumferential downstream flange and the downstream annular tab.
  • An annular cavity is defined between the ring and the housing and defined upstream and downstream by the annular tabs of the housing.
  • the upstream annular lug comprises orifices supplying this cavity with air taken from a compression stage of the turbomachine.
  • each ring sector expands and deforms by taking a concave curved shape in the circumferential direction, with an outward facing concavity (decampling phenomenon).
  • the formation of radial spacings between the annular tab downstream of the casing and the circumferential rims downstream of the ring sectors is observed.
  • the sealing of the downstream fastener between the circumferential downstream flange of the ring and the annular downstream lug of the casing is achieved by axial prestressing of the annular lug. downstream on a radial face of the downstream circumferential flange which is opposite to the locking member.
  • this assembly with cold axial prestressing is not conceivable in the case of a composite ring because of its high rigidity and low thermal expansion.
  • the invention aims in particular to provide a simple, economical and effective solution to these problems, to avoid the disadvantages of the known technique.
  • a turbine stage for a turbomachine comprising a paddle wheel rotating inside a sectorized ring of composite material carried by a housing, each ring sector comprising a downstream circumferential rim held in support. radial on an annular lug of the housing by a lock C, characterized in that the annular lug of the housing is engaged radially in an annular groove of the circumferential rim downstream of the ring with a cold axial clearance defined to cancel hot in operation and allow axial tight sealing of the annular lug of the housing in the annular groove of the ring sector.
  • the sealing of the circumferential rim downstream of the ring in operation is ensured by the axial clamping of the upstream and downstream ends of the annular tab downstream of the casing in the annular groove, due to the greater expansion of the casing. compared to the composite ring.
  • the concave curvature of the ring and its downstream circumferential rim is thus compensated for by the axial tightening of the annular lug guaranteeing the sealing of the downstream fastening of the ring.
  • the annular lug of the housing comprises upstream and downstream radial faces intended to come into hot abutment on the radial flanks of the groove.
  • the radial faces of the annular tab and the radial flanks of the groove retain their radial shape ensuring an annular contact between the radial faces of the ring and the radial flanks of the groove.
  • the aforementioned cold axial play is of the order of one-tenth of a millimeter. It is also possible to provide an annular sealing ring housed in an annular groove of the face of the annular flange which is applied to the bottom of the annular groove of the ring sector.
  • the composite material is of the ceramic matrix type and the casing is made of metallic material.
  • the invention also relates to a turbomachine, such as an airplane turbojet or turboprop, comprising a high pressure turbine stage of the type described above.
  • FIG. 1 is a partial schematic view in axial section of a turbine stage according to the prior art
  • FIG. 2 is a schematic cross-sectional view along the cutting plane A-A shown in Figure 1;
  • FIG. 3 is a partial schematic view in axial section of a cold turbine stage according to the invention and in a sectional plane not passing through a locking member;
  • FIG. 4 is a partial schematic view in axial section of a hot turbine stage according to the invention and in a section plane passing through a locking member.
  • FIG. 1 represents a part of a turbine stage 10 in a turbomachine which comprises a distributor stage comprising a plurality of stationary vanes and arranged upstream of a mobile wheel comprising a plurality of vanes and rotating inside a ring 12 carried by an outer casing 14.
  • the ring 12 is formed of a plurality of substantially cylindrical ring sectors juxtaposed circumferentially end to end.
  • Each ring sector comprises a cylindrical portion 16 bearing on its inner face a seal 18 of abradable material cooperating with the outer peripheries of the vanes of the rotor wheel.
  • Each ring sector comprises two upstream annular tabs 18 and downstream hooking 20 on the casing 14.
  • the outer end of the upstream annular tab 18 comprises a circumferential flange 22 facing upstream and axially engaged in an annular groove 24 downstream formed in a radial annular tab 26 of the housing.
  • the outer end of the downstream annular tab 20 of the ring comprises a circumferential rim 28 oriented downstream and radially clamped on a cylindrical portion 30 of an annular tab 32 of the casing 14 by means of a locking member 32 with a section at C engaged axially on the downstream circumferential flange 28 and on the cylindrical portion 30 of the downstream annular tab 32 of the casing 14.
  • Each downstream circumferential rim 20 of a ring sector comprises at least one notch aligned radially with a notch of the cylindrical portion 30 of the annular tab 32 downstream of the casing 14 and whose width is sufficient to allow the axial engagement of the locking member 32 and fixing the ring 12 on the casing 14.
  • An annular cavity 34 is defined between the segmented ring 12 and the casing 14 and delimited upstream by the upstream annular tabs 18, 26 of the ring 14 and the casing 14, respectively, and downstream by the downstream annular tabs 20, 32 of the ring 12 and the casing 14, respectively.
  • the upstream annular lug 26 of the casing 14 comprises orifices 36 for the passage of cooling air coming from a space that bypasses the combustion chamber, that is to say air circulating between the outer casing of the casing 14. combustion chamber and the outer wall of revolution of the combustion chamber.
  • an annular sealing ring 38 is mounted in an annular groove 40 of the inner face of the cylindrical portion 30. This rod 38 is compressed radially in the annular groove 40 and on the downstream circumferential rim 28 of the ring 12.
  • the inner face of the cylindrical portion 30 comprises a rib 42 engaged radially in an annular recess of the downstream circumferential flange 28 of the ring 12 to ensure the axial locking of the ring 12 on the casing 14.
  • each ring sector each comprise three slots 44, 46, 48 each housing a sealing strip.
  • a first slot 44 is formed in the cylindrical portion 16 of the ring 12 and extends substantially the entire length of the ring 12 and is parallel to the longitudinal axis of the ring 12.
  • the other two slots 46, 48 are oblique and each formed in the upstream annular lug 18 and the downstream annular lug 20 of the ring, respectively.
  • the radially inner ends of the two slits 46, 48 oblique open in a middle portion of the longitudinal slot 44 and their radial ends open at the outer faces of the upstream and downstream circumferential rims 22 and 28.
  • Each slat is inserted halfway into a slot 44. , 46, 48 of a sector and for the other half in a corresponding slot facing vis-à-vis formed in a radial face of an adjacent ring sector.
  • each composite ring sector deforms under the effect of heat and adopts a concave curved shape with concavity facing outwards ( Figure 2).
  • the housing 14 is also deformed and has circumferential corrugations.
  • the invention overcomes this problem as well as those mentioned above by forming an annular groove 50 in the outer cylindrical face of the downstream circumferential flange 52 of the ring 54, in which is engaged radially the downstream cylindrical portion 55 of the downstream annular lug 56 of the casing 14 with a cold axial play designed to cancel in operation due to the greater expansion of the casing 14 and its downstream annular lug 56 relative to the expansion of the ring 54 in composite ( Figure 3).
  • the annular groove 50 comprises two upstream and downstream radial annular flanks 58 and 60.
  • the downstream cylindrical portion 55 of the downstream annular lug 56 of the casing 14 comprises two upstream and downstream radial faces 64 and 64.
  • the radial faces 62, 64 the downstream annular tab 56 of the casing 14 bear against the radial flanks 58, 60 of the groove 50, due to the differential expansion between the composite ring 54 and the casing 14, which ensures axial clamping of the annular tab 56 in the groove 50 and provides a sealing air ventilation circulating in the cavity 34. This axial clamping ensures at the same time the axial locking of the ring 54 on the casing 14.
  • the depth of the groove 50 is chosen to be greater than the maximum radial difference R in operation between the inner face 66 of the downstream cylindrical portion 55 of the downstream lug 56 of the casing 14 and the bottom wall 68 of the groove 50, in order to permanently ensure a tight axial tight heat and avoid axial separation of the ring 54 relative to the housing 14.
  • the mounting of a ring sector is achieved by inserting the upstream circumferential flange 22 of the ring 54 in the annular groove of the upstream leg 18 of the housing 14 and the downstream end of the ring is tilted outwards so that the cylindrical portion 55 is applied in the bottom of the groove 50.
  • the axial play j cold facilitates the outward tilting of the ring 54 on the casing 14.
  • An annular ring 38 is housed in an annular groove 40 of the face 66 of the downstream annular tab 56 of the housing which is applied to the bottom 68 of the groove 50.
  • each downstream circumferential rim 52 of a ring sector comprises a notch aligned radially with a notch in the cylindrical portion of the annular downstream lug of the casing for axial mounting of the locking member 32 with a C-section.
  • inter-sector sealing means are similar to those of the prior art. It will be noted, however, that according to the invention, the oblique slot of the downstream annular tab 64 of the ring 54 opens into the groove 50 and at the level of the ring 38.
  • the cold axial play is of the order of 0.1 millimeter.
  • the ring 54 may be made of ceramic matrix composite material resistant to high temperatures such as those in a high pressure turbine and the housing 14 is made of a metal material such as INCO or steel.

Landscapes

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

Abstract

The invention relates to a turbine stage for a turbine engine, including an impeller rotating inside a sectorised ring (54) made of a composite material supported by a housing (14), each ring sector including a downstream circumferential edge (52) held radially resting on an annular tab (56) which is radially inserted in an annular groove (50) of the downstream circumferential edge (52) of the ring (54) having axial play when cold, defined to be cancelled out when hot during operation and to allow sealed axial clamping of the annular tab (56) of the housing (14) in the annular groove (50) of the ring sector.

Description

ETAGE DE TURBINE DANS UNE TURBOMACHINE  TURBINE STAGE IN A TURBOMACHINE
La présente invention concerne un étage de turbine dans une turbomachine telle qu'un turboréacteur ou un turbopropulseur. The present invention relates to a turbine stage in a turbomachine such as a turbojet engine or a turboprop engine.
Une turbomachine comprend essentiellement d'amont en aval un compresseur, une chambre de combustion et une turbine, le compresseur alimentant la chambre de combustion en air sous pression, et la turbine recevant les gaz chauds provenant de la chambre de combustion pour en extraire de l'énergie.  A turbomachine essentially comprises, from upstream to downstream, a compressor, a combustion chamber and a turbine, the compressor supplying the combustion chamber with pressurized air, and the turbine receiving the hot gases coming from the combustion chamber to extract them from the combustion chamber. 'energy.
Classiquement, un étage de turbine basse pression comprend un redresseur formé d'une rangée annulaire d'aubes fixes s'étendant radialement entre deux plates-formes annulaires interne et externe et une roue de rotor montée en aval du redresseur à l'intérieur d'un anneau sectorisé porté par un carter entourant l'étage de turbine.  Conventionally, a low-pressure turbine stage comprises a rectifier formed of an annular row of stationary vanes extending radially between two inner and outer annular platforms and a rotor wheel mounted downstream of the rectifier inside. a sectorized ring carried by a casing surrounding the turbine stage.
Chaque secteur d'anneau porte sur une face interne une garniture d'étanchéité coopérant avec les périphéries externes des aubes de la roue de rotor et comprend sur une face externe des moyens d'accrochage sur le carter formés par des rebords circonférentiels amont et aval. Le rebord circonférentiel amont est engagé axialement dans une gorge annulaire portée par une patte annulaire amont du carter et le rebord circonférentiel aval est serré radialement sur une patte annulaire aval du carter par un organe de verrouillage à section en C engagé axialement depuis l'aval sur le rebord circonférentiel aval et la patte annulaire aval.  Each ring sector carries on an inner face a seal cooperating with the outer peripheries of the vanes of the rotor wheel and comprises on an outer face of the attachment means on the housing formed by upstream and downstream circumferential rims. The upstream circumferential flange is engaged axially in an annular groove carried by an upstream annular tab of the casing and the downstream circumferential flange is clamped radially on an annular tab downstream of the casing by a C-section locking member axially engaged from downstream on the circumferential downstream flange and the downstream annular tab.
Une cavité annulaire est définie entre l'anneau et le carter et délimitée en amont et aval par les pattes annulaires du carter. La patte annulaire amont comprend des orifices alimentant cette cavité en air prélevé sur un étage de compression de la turbomachine.  An annular cavity is defined between the ring and the housing and defined upstream and downstream by the annular tabs of the housing. The upstream annular lug comprises orifices supplying this cavity with air taken from a compression stage of the turbomachine.
L'introduction d'air de refroidissement dans une cavité au droit de l'anneau de turbine permet d'éviter une ouverture importante du jeu en sommet d'aubes, c'est-à-dire entre les extrémités radialement externes des aubes et la garniture d'étanchéité, pour minimiser le passage d'air sous pression en dehors de la zone balayée par les aubes et éviter ainsi que les performances de la turbine ne soient pénalisées. The introduction of cooling air into a cavity in line with the turbine ring makes it possible to prevent a large opening of the clearance at the top of the blades, that is to say between the radially outer ends of the blades and the seal, to minimize the passage of air under pressure outside the area swept by the blades and thus avoid the performance of the turbine are penalized.
Il est connu de réaliser les secteurs d'anneau en matériau composite à matrice céramique pour tirer parti de leurs bonnes propriétés mécaniques à des températures élevées tandis que le carter est généralement réalisé dans un matériau métallique. L'anneau est donc plus rigide que le carter et possède un coefficient de dilatation thermique inférieur à celui du carter métallique, ce qui conduit à des différences de dilatation entre l'anneau et le carter.  It is known to make the ceramic matrix composite ring sectors to take advantage of their good mechanical properties at high temperatures while the casing is generally made of a metallic material. The ring is therefore more rigid than the casing and has a coefficient of thermal expansion less than that of the metal casing, which leads to differences in expansion between the ring and the casing.
Dans sa demande FR0951446, la demanderesse a proposé de bloquer axialement l'anneau sur la patte annulaire aval par engagement radial de formes complémentaires prévues sur l'anneau et sur la patte annulaire, un jonc annulaire étant monté dans une gorge annulaire d'une face de la patte annulaire en regard du rebord circonférentiel aval de l'anneau et compressé sur ce rebord.  In its application FR0951446, the applicant proposed to axially lock the ring on the downstream annular lug by radial engagement of complementary shapes provided on the ring and on the annular lug, an annular ring being mounted in an annular groove of a face the annular tab facing the circumferential rim downstream of the ring and compressed on this flange.
Toutefois, en fonctionnement, chaque secteur d'anneau se dilate et se déforme en prenant une forme incurvée concave dans la direction circonférentielle, avec une concavité tournée vers l'extérieur (phénomène de décambrage). Ainsi, on observe la formation d'espacements radiaux entre la patte annulaire aval du carter et les rebords circonférentiels aval des secteurs d'anneau.  However, in operation, each ring sector expands and deforms by taking a concave curved shape in the circumferential direction, with an outward facing concavity (decampling phenomenon). Thus, the formation of radial spacings between the annular tab downstream of the casing and the circumferential rims downstream of the ring sectors is observed.
Ces espacements radiaux sont tels que le jonc annulaire s'avère insuffisant pour réaliser l'étanchéité du rebord circonférentiel aval sur la patte annulaire du carter et des fuites d'air de refroidissement se produisent entre les rebords circonférentiels aval des secteurs d'anneau et la patte annulaire aval du carter.  These radial spacings are such that the annular ring is insufficient to seal the downstream circumferential rim on the annular lug of the housing and cooling air leaks occur between the circumferential edges downstream of the ring sectors and the annular tab downstream of the housing.
Dans d'autres réalisations où l'anneau n'est pas en matériau composite, l'étanchéité de la fixation aval entre le rebord circonférentiel aval de l'anneau et la patte annulaire aval du carter est réalisée par une précontrainte axiale de la patte annulaire aval sur une face radiale du rebord circonférentiel aval qui est opposée à l'organe de verrouillage. Cependant, ce montage avec précontrainte axiale à froid n'est pas envisageable dans le cas d'un anneau en composite du fait de sa rigidité importante et de sa faible dilatation thermique. In other embodiments in which the ring is not made of composite material, the sealing of the downstream fastener between the circumferential downstream flange of the ring and the annular downstream lug of the casing is achieved by axial prestressing of the annular lug. downstream on a radial face of the downstream circumferential flange which is opposite to the locking member. However, this assembly with cold axial prestressing is not conceivable in the case of a composite ring because of its high rigidity and low thermal expansion.
L'invention a notamment pour but d'apporter une solution simple, économique et efficace à ces problèmes, permettant d'éviter les inconvénients de la technique connue.  The invention aims in particular to provide a simple, economical and effective solution to these problems, to avoid the disadvantages of the known technique.
A cette fin, elle propose un étage de turbine pour une turbomachine, comprenant une roue à aubes tournant à l'intérieur d'un anneau sectorisé en matériau composite porté par un carter, chaque secteur d'anneau comprenant un rebord circonférentiel aval maintenu en appui radial sur une patte annulaire du carter par un verrou en C, caractérisé en ce que la patte annulaire du carter est engagée radialement dans une rainure annulaire du rebord circonférentiel aval de l'anneau avec un jeu axial à froid défini pour s'annuler à chaud en fonctionnement et permettre un serrage axial étanche de la patte annulaire du carter dans la rainure annulaire du secteur d'anneau.  To this end, it proposes a turbine stage for a turbomachine, comprising a paddle wheel rotating inside a sectorized ring of composite material carried by a housing, each ring sector comprising a downstream circumferential rim held in support. radial on an annular lug of the housing by a lock C, characterized in that the annular lug of the housing is engaged radially in an annular groove of the circumferential rim downstream of the ring with a cold axial clearance defined to cancel hot in operation and allow axial tight sealing of the annular lug of the housing in the annular groove of the ring sector.
Selon l'invention, l'étanchéité du rebord circonférentiel aval de l'anneau en fonctionnement est assurée par le serrage axial des extrémités amont et aval de la patte annulaire aval du carter dans la rainure annulaire, du fait de la dilatation plus importante du carter par rapport à l'anneau en composite. La courbure concave de l'anneau et de son rebord circonférentiel aval est ainsi compensée par le serrage axial de la patte annulaire garantissant l'étanchéité de la fixation aval de l'anneau.  According to the invention, the sealing of the circumferential rim downstream of the ring in operation is ensured by the axial clamping of the upstream and downstream ends of the annular tab downstream of the casing in the annular groove, due to the greater expansion of the casing. compared to the composite ring. The concave curvature of the ring and its downstream circumferential rim is thus compensated for by the axial tightening of the annular lug guaranteeing the sealing of the downstream fastening of the ring.
Avantageusement, la patte annulaire du carter comprend des faces radiales amont et aval destinées à venir en appui à chaud sur des flancs radiaux de la rainure. En fonctionnement, les faces radiales de la patte annulaire et les flancs radiaux de la rainure conservent leur forme radiale assurant un contact annulaire entre les faces radiales de l'anneau et les flancs radiaux de la rainure.  Advantageously, the annular lug of the housing comprises upstream and downstream radial faces intended to come into hot abutment on the radial flanks of the groove. In operation, the radial faces of the annular tab and the radial flanks of the groove retain their radial shape ensuring an annular contact between the radial faces of the ring and the radial flanks of the groove.
Selon une autre caractéristique de l'invention, le jeu axial précité à froid est de l'ordre du dixième de millimètre. Il est également possible de prévoir un jonc annulaire d'étanchéité logé dans une gorge annulaire de la face de la patte annulaire qui est appliquée sur le fond de la rainure annulaire du secteur d'anneau. According to another characteristic of the invention, the aforementioned cold axial play is of the order of one-tenth of a millimeter. It is also possible to provide an annular sealing ring housed in an annular groove of the face of the annular flange which is applied to the bottom of the annular groove of the ring sector.
Avantageusement, le matériau composite est du type à matrice céramique et le carter est réalisé en matériau métallique.  Advantageously, the composite material is of the ceramic matrix type and the casing is made of metallic material.
L'invention concerne également une turbomachine, telle qu'un turboréacteur ou un turbopropulseur d'avion, comprenant un étage de turbine haute pression du type décrit précédemment.  The invention also relates to a turbomachine, such as an airplane turbojet or turboprop, comprising a high pressure turbine stage of the type described above.
L'invention sera mieux comprise et d'autres détails, avantages et caractéristiques de l'invention apparaîtront à la lecture de la description suivante faite à titre d'exemple non limitatif, en référence aux dessins annexés dans lesquels :  The invention will be better understood and other details, advantages and features of the invention will appear on reading the following description given by way of non-limiting example, with reference to the accompanying drawings in which:
- la figure 1 est une vue schématique partielle en coupe axiale d'un étage de turbine selon la technique antérieure ;  - Figure 1 is a partial schematic view in axial section of a turbine stage according to the prior art;
- la figure 2 est une vue schématique en coupe transversale selon le plan de coupe A-A indiqué sur la figure 1 ; - Figure 2 is a schematic cross-sectional view along the cutting plane A-A shown in Figure 1;
- la figure 3 est une vue schématique partielle en coupe axiale d'un étage de turbine à froid selon l'invention et selon un plan de coupe ne passant pas par un organe de verrouillage ;  - Figure 3 is a partial schematic view in axial section of a cold turbine stage according to the invention and in a sectional plane not passing through a locking member;
- la figure 4 est une vue schématique partielle en coupe axiale d'un étage de turbine à chaud selon l'invention et selon un plan de coupe passant par un organe de verrouillage. - Figure 4 is a partial schematic view in axial section of a hot turbine stage according to the invention and in a section plane passing through a locking member.
On se réfère tout d'abord à la figure 1 qui représente une partie d'un étage de turbine 10 dans une turbomachine qui comprend un étage distributeur comportant une pluralité d'aubes fixes et agencé en amont d'une roue mobile comportant une pluralité d'aubes et tournant à l'intérieur d'un anneau 12 porté par un carter externe 14.  Referring firstly to FIG. 1 which represents a part of a turbine stage 10 in a turbomachine which comprises a distributor stage comprising a plurality of stationary vanes and arranged upstream of a mobile wheel comprising a plurality of vanes and rotating inside a ring 12 carried by an outer casing 14.
L'anneau 12 est formé d'une pluralité de secteurs d'anneau sensiblement cylindriques juxtaposés circonférentiellement bout à bout. Chaque secteur d'anneau comprend une partie cylindrique 16 portant sur sa face interne une garniture d'étanchéité 18 en matériau abradable coopérant avec les périphéries externes des aubes de la roue de rotor. Chaque secteur d'anneau comprend deux pattes annulaires amont 18 et aval 20 d'accrochage sur le carter 14. L'extrémité externe de la patte annulaire amont 18 comprend un rebord circonférentiel 22 orienté vers l'amont et engagé axialement dans une gorge annulaire 24 tournée vers l'aval formée dans une patte annulaire radiale 26 du carter. L'extrémité externe de la patte annulaire aval 20 de l'anneau comprend un rebord circonférentiel 28 orienté vers l'aval et serré radialement sur une partie cylindrique 30 d'une patte annulaire 32 du carter 14 grâce à un organe de verrouillage 32 à section en C engagé axialement sur le rebord circonférentiel aval 28 et sur la partie cylindrique 30 de la patte annulaire aval 32 du carter 14. The ring 12 is formed of a plurality of substantially cylindrical ring sectors juxtaposed circumferentially end to end. Each ring sector comprises a cylindrical portion 16 bearing on its inner face a seal 18 of abradable material cooperating with the outer peripheries of the vanes of the rotor wheel. Each ring sector comprises two upstream annular tabs 18 and downstream hooking 20 on the casing 14. The outer end of the upstream annular tab 18 comprises a circumferential flange 22 facing upstream and axially engaged in an annular groove 24 downstream formed in a radial annular tab 26 of the housing. The outer end of the downstream annular tab 20 of the ring comprises a circumferential rim 28 oriented downstream and radially clamped on a cylindrical portion 30 of an annular tab 32 of the casing 14 by means of a locking member 32 with a section at C engaged axially on the downstream circumferential flange 28 and on the cylindrical portion 30 of the downstream annular tab 32 of the casing 14.
Chaque rebord circonférentiel aval 20 d'un secteur d'anneau comprend au moins une encoche alignée radialement avec une encoche de la partie cylindrique 30 de la patte annulaire 32 aval du carter 14 et dont la largeur est suffisante pour permettre l'engagement axial de l'organe de verrouillage 32 et la fixation de l'anneau 12 sur le carter 14.  Each downstream circumferential rim 20 of a ring sector comprises at least one notch aligned radially with a notch of the cylindrical portion 30 of the annular tab 32 downstream of the casing 14 and whose width is sufficient to allow the axial engagement of the locking member 32 and fixing the ring 12 on the casing 14.
Une cavité annulaire 34 est définie entre l'anneau 12 sectorisé et le carter 14 et délimitée en amont par les pattes annulaires amont 18, 26 de l'anneau 14 et du carter 14, respectivement, et en aval par les pattes annulaires aval 20, 32 de l'anneau 12 et du carter 14, respectivement.  An annular cavity 34 is defined between the segmented ring 12 and the casing 14 and delimited upstream by the upstream annular tabs 18, 26 of the ring 14 and the casing 14, respectively, and downstream by the downstream annular tabs 20, 32 of the ring 12 and the casing 14, respectively.
La patte annulaire amont 26 du carter 14 comprend des orifices 36 de passage d'air de refroidissement provenant d'un espace de contournement de la chambre de combustion, c'est-à-dire de l'air circulant entre le carter externe de la chambre de combustion et la paroi de révolution externe de la chambre de combustion. Pour éviter des fuites d'air de refroidissement entre la partie cylindrique 30 de la patte annulaire aval 32 du carter 14 et le rebord circonférentiel aval 20 de l'anneau 12, un jonc annulaire d'étanchéité 38 est monté dans une gorge annulaire 40 de la face interne de la partie cylindrique 30. Ce jonc 38 est comprimé radialement dans la gorge annulaire 40 et sur le rebord circonférentiel aval 28 de l'anneau 12. La face interne de la partie cylindrique 30 comprend une nervure 42 engagée radialement dans un évidement annulaire du rebord circonférentiel aval 28 de l'anneau 12 pour assurer le blocage axial de l'anneau 12 sur le carter 14. The upstream annular lug 26 of the casing 14 comprises orifices 36 for the passage of cooling air coming from a space that bypasses the combustion chamber, that is to say air circulating between the outer casing of the casing 14. combustion chamber and the outer wall of revolution of the combustion chamber. To prevent cooling air leaks between the cylindrical portion 30 of the downstream annular tab 32 of the casing 14 and the downstream circumferential rim 20 of the ring 12, an annular sealing ring 38 is mounted in an annular groove 40 of the inner face of the cylindrical portion 30. This rod 38 is compressed radially in the annular groove 40 and on the downstream circumferential rim 28 of the ring 12. The inner face of the cylindrical portion 30 comprises a rib 42 engaged radially in an annular recess of the downstream circumferential flange 28 of the ring 12 to ensure the axial locking of the ring 12 on the casing 14.
Les faces radiales des extrémités circonférentielles de chaque secteur d'anneau comprennent chacune trois fentes 44, 46, 48 logeant chacune une lamelle d'étanchéité. Une première fente 44 est formée dans la partie cylindrique 16 de l'anneau 12 et s'étend sensiblement sur toute la longueur de l'anneau 12 et est parallèle à l'axe longitudinal de l'anneau 12. Les deux autres fentes 46, 48 sont obliques et formées chacune dans la patte annulaire amont 18 et la patte annulaire aval 20 de l'anneau, respectivement. Les extrémités radialement internes des deux fentes 46, 48 obliques débouchent dans une partie médiane de la fente longitudinale 44 et leurs extrémités radiales débouchent au niveau des faces externes des rebords circonférentiels amont 22 et aval 28. Chaque lamelle est insérée pour moitié dans une fente 44, 46, 48 d'un secteur et pour l'autre moitié dans une fente correspondante en vis-à-vis formée dans une face radiale d'un secteur d'anneau adjacent.  The radial faces of the circumferential ends of each ring sector each comprise three slots 44, 46, 48 each housing a sealing strip. A first slot 44 is formed in the cylindrical portion 16 of the ring 12 and extends substantially the entire length of the ring 12 and is parallel to the longitudinal axis of the ring 12. The other two slots 46, 48 are oblique and each formed in the upstream annular lug 18 and the downstream annular lug 20 of the ring, respectively. The radially inner ends of the two slits 46, 48 oblique open in a middle portion of the longitudinal slot 44 and their radial ends open at the outer faces of the upstream and downstream circumferential rims 22 and 28. Each slat is inserted halfway into a slot 44. , 46, 48 of a sector and for the other half in a corresponding slot facing vis-à-vis formed in a radial face of an adjacent ring sector.
Toutefois, comme expliqué précédemment, chaque secteur d'anneau en composite se déforme sous l'effet de la chaleur et adopte une forme incurvée concave à concavité tournée vers l'extérieur (figure 2). Le carter 14 subit également une déformation et comporte des ondulations circonférentielles. Il s'ensuit, du fait des dilatations différentielles entre l'anneau 12 en composite et le carter 14, la formation d'un espace radial R entre chaque rebord circonférentiel 28 et la partie cylindrique 30 d'une patte aval 32 du carter 14 conduisant à des fuites de l'air de ventilation de la cavité annulaire 34 vers la veine de gaz de la turbine.  However, as previously explained, each composite ring sector deforms under the effect of heat and adopts a concave curved shape with concavity facing outwards (Figure 2). The housing 14 is also deformed and has circumferential corrugations. As a result, due to the differential expansion between the composite ring 12 and the casing 14, the formation of a radial space R between each circumferential flange 28 and the cylindrical portion 30 of a downstream lug 32 of the housing 14 leading to leakage of the ventilation air from the annular cavity 34 to the gas stream of the turbine.
L'invention permet de remédier à ce problème ainsi qu'à ceux mentionnés précédemment en formant une rainure annulaire 50 dans la face cylindrique externe du rebord circonférentiel aval 52 de l'anneau 54, dans laquelle est engagée radialement la partie cylindrique aval 55 de la patte annulaire aval 56 du carter 14 avec un jeu axial j à froid destiné à s'annuler en fonctionnement du fait de la dilatation plus importante du carter 14 et de sa patte annulaire aval 56 par rapport à la dilatation de l'anneau 54 en composite (figure 3). The invention overcomes this problem as well as those mentioned above by forming an annular groove 50 in the outer cylindrical face of the downstream circumferential flange 52 of the ring 54, in which is engaged radially the downstream cylindrical portion 55 of the downstream annular lug 56 of the casing 14 with a cold axial play designed to cancel in operation due to the greater expansion of the casing 14 and its downstream annular lug 56 relative to the expansion of the ring 54 in composite (Figure 3).
La rainure annulaire 50 comprend deux flancs annulaires radiaux amont 58 et aval 60. La partie cylindrique aval 55 de la patte annulaire aval 56 du carter 14 comprend deux faces radiales amont 62 et aval 64. En fonctionnement à chaud, les faces radiales 62, 64 de la patte annulaire aval 56 du carter 14 viennent en appui sur les flancs radiaux 58, 60 de la rainure 50, du fait de la dilatation différentielle entre l'anneau 54 en composite et le carter 14, ce qui assure un serrage axial de la patte annulaire 56 dans la rainure 50 et réalise une étanchéité à l'air de ventilation circulant dans la cavité 34. Ce serrage axial permet d'assurer en même temps le blocage axial de l'anneau 54 sur le carter 14.  The annular groove 50 comprises two upstream and downstream radial annular flanks 58 and 60. The downstream cylindrical portion 55 of the downstream annular lug 56 of the casing 14 comprises two upstream and downstream radial faces 64 and 64. In hot operation, the radial faces 62, 64 the downstream annular tab 56 of the casing 14 bear against the radial flanks 58, 60 of the groove 50, due to the differential expansion between the composite ring 54 and the casing 14, which ensures axial clamping of the annular tab 56 in the groove 50 and provides a sealing air ventilation circulating in the cavity 34. This axial clamping ensures at the same time the axial locking of the ring 54 on the casing 14.
La profondeur de la rainure 50 est choisie de manière à être supérieure à l'écart radial R maximal en fonctionnement entre la face interne 66 de la partie cylindrique aval 55 de la patte aval 56 du carter 14 et la paroi de fond 68 de la rainure 50, afin d'assurer en permanence un serrage axial étanche à chaud et éviter une désolidarisation axiale de l'anneau 54 par rapport au carter 14.  The depth of the groove 50 is chosen to be greater than the maximum radial difference R in operation between the inner face 66 of the downstream cylindrical portion 55 of the downstream lug 56 of the casing 14 and the bottom wall 68 of the groove 50, in order to permanently ensure a tight axial tight heat and avoid axial separation of the ring 54 relative to the housing 14.
Le montage d'un secteur d'anneau est réalisé en insérant le rebord circonférentiel amont 22 de l'anneau 54 dans la gorge annulaire de la patte amont 18 du carter 14 puis l'extrémité aval de l'anneau est basculée vers l'extérieur pour que la partie cylindrique 55 s'applique dans le fond de la rainure 50. Le jeu axial j à froid permet de faciliter le basculement vers l'extérieur de l'anneau 54 sur le carter 14.  The mounting of a ring sector is achieved by inserting the upstream circumferential flange 22 of the ring 54 in the annular groove of the upstream leg 18 of the housing 14 and the downstream end of the ring is tilted outwards so that the cylindrical portion 55 is applied in the bottom of the groove 50. The axial play j cold facilitates the outward tilting of the ring 54 on the casing 14.
Un jonc annulaire 38 est logé dans une gorge annulaire 40 de la face 66 de la patte annulaire aval 56 du carter qui est appliquée sur le fond 68 de la rainure 50.  An annular ring 38 is housed in an annular groove 40 of the face 66 of the downstream annular tab 56 of the housing which is applied to the bottom 68 of the groove 50.
De manière similaire à la technique antérieure, chaque rebord circonférentiel aval 52 d'un secteur d'anneau comprend une encoche alignée radialement avec une encoche de la partie cylindrique de la patte annulaire aval du carter pour le montage axial de l'organe de verrouillage 32 à section en C. In a similar manner to the prior art, each downstream circumferential rim 52 of a ring sector comprises a notch aligned radially with a notch in the cylindrical portion of the annular downstream lug of the casing for axial mounting of the locking member 32 with a C-section.
Les moyens d'étanchéité inter-secteurs sont similaires à ceux de la technique antérieure. On notera toutefois, que selon l'invention, la fente oblique de la patte annulaire aval 64 de l'anneau 54 débouche dans la rainure 50 et au niveau du jonc 38.  The inter-sector sealing means are similar to those of the prior art. It will be noted, however, that according to the invention, the oblique slot of the downstream annular tab 64 of the ring 54 opens into the groove 50 and at the level of the ring 38.
Dans une réalisation particulière de l'invention, le jeu axial à froid est de l'ordre de 0,1 millimètre.  In a particular embodiment of the invention, the cold axial play is of the order of 0.1 millimeter.
L'anneau 54 peut être réalisé en matériau composite à matrice céramique résistant bien aux températures élevées telles que celles régnant dans une turbine haute pression et le carter 14 est réalisé dans un matériau métallique tel que de l'INCO ou de l'acier.  The ring 54 may be made of ceramic matrix composite material resistant to high temperatures such as those in a high pressure turbine and the housing 14 is made of a metal material such as INCO or steel.

Claims

REVENDICATIONS
1 . Etage de turbine pour une turbomachine, comprenant une roue à aubes tournant à l'intérieur d'un anneau sectorisé (54) en matériau composite porté par un carter (14), chaque secteur d'anneau comprenant un rebord circonférentiel aval (52) maintenu en appui radial sur une patte annulaire (56) du carter (14) par un verrou en C, caractérisé en ce que la patte annulaire (56) du carter (14) est engagée radialement dans une rainure annulaire (50) du rebord circonférentiel aval (52) de l'anneau (54) avec un jeu axial à froid défini pour s'annuler à chaud en fonctionnement et permettre un serrage axial étanche de la patte annulaire (56) du carter (14) dans la rainure annulaire (50) du secteur d'anneau. 1. Turbine stage for a turbomachine, comprising an impeller rotating inside a sectorized ring (54) of composite material carried by a housing (14), each ring sector comprising a downstream circumferential rim (52) maintained in radial support on an annular lug (56) of the casing (14) by a latch in C, characterized in that the annular lug (56) of the casing (14) is engaged radially in an annular groove (50) of the downstream circumferential rim (52) of the ring (54) with cold axial backlash defined to cancel hot during operation and allow axial tight sealing of the annular lug (56) of the housing (14) in the annular groove (50) of the ring area.
2. Etage de turbine selon la revendication 1 , caractérisé en ce que la patte annulaire (56) du carter (14) comprend des faces radiales amont (62) et aval (64) destinées à venir en appui à chaud sur des flancs radiaux (58, 60) de la rainure (50).  2. turbine stage according to claim 1, characterized in that the annular lug (56) of the casing (14) comprises upstream radial faces (62) and downstream (64) intended to come into hot abutment on radial flanks ( 58, 60) of the groove (50).
3. Etage de turbine selon la revendication 1 ou 2, caractérisé en ce que le jeu axial à froid est de l'ordre du dixième de millimètre.  3. Turbine stage according to claim 1 or 2, characterized in that the cold axial play is of the order of one-tenth of a millimeter.
4. Etage de turbine selon l'une des revendications précédentes, caractérisé en ce qu'un jonc annulaire (38) d'étanchéité est logé dans une gorge annulaire (40) de la face (66) de la patte annulaire qui est appliquée sur le fond (68) de la rainure annulaire (50) du secteur d'anneau.  4. Turbine stage according to one of the preceding claims, characterized in that an annular ring (38) sealing is housed in an annular groove (40) of the face (66) of the annular tab which is applied on the bottom (68) of the annular groove (50) of the ring sector.
5. Etage de turbine selon l'une des revendications précédentes, caractérisé en ce que le matériau composite est du type à matrice céramique et le carter (14) est réalisé en matériau métallique.  5. Turbine stage according to one of the preceding claims, characterized in that the composite material is of the ceramic matrix type and the housing (14) is made of metal material.
6. Turbomachine, telle qu'un turboréacteur ou un turbopropulseur d'avion, caractérisée en ce qu'elle comprend un étage de turbine haute pression selon l'une des revendications 1 à 5.  6. Turbomachine, such as a jet engine or a turboprop engine, characterized in that it comprises a high pressure turbine stage according to one of claims 1 to 5.
EP10809013A 2009-12-18 2010-12-14 Turbine stage of a turbine engine Withdrawn EP2513428A1 (en)

Applications Claiming Priority (2)

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FR0906162A FR2954400B1 (en) 2009-12-18 2009-12-18 TURBINE STAGE IN A TURBOMACHINE
PCT/FR2010/052721 WO2011073570A1 (en) 2009-12-18 2010-12-14 Turbine stage of a turbine engine

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BR (1) BR112012010257A2 (en)
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US20120237342A1 (en) 2012-09-20
CA2777370A1 (en) 2011-06-23
CN102667066A (en) 2012-09-12
FR2954400A1 (en) 2011-06-24
RU2012130351A (en) 2014-01-27
BR112012010257A2 (en) 2016-03-29
WO2011073570A1 (en) 2011-06-23

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