[go: up one dir, main page]
More Web Proxy on the site http://driver.im/

EP3797213A1 - Angular sector for turbomachine blading with improved sealing - Google Patents

Angular sector for turbomachine blading with improved sealing

Info

Publication number
EP3797213A1
EP3797213A1 EP19740611.9A EP19740611A EP3797213A1 EP 3797213 A1 EP3797213 A1 EP 3797213A1 EP 19740611 A EP19740611 A EP 19740611A EP 3797213 A1 EP3797213 A1 EP 3797213A1
Authority
EP
European Patent Office
Prior art keywords
sector
block
angular
sectors
crown
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.)
Granted
Application number
EP19740611.9A
Other languages
German (de)
French (fr)
Other versions
EP3797213B1 (en
Inventor
Thomas Nolwenn Emmanuel DELAHAYE
Kamel Benderradji
Alain Marc Lucien Bromann
Liliana GOMES PEREIRA
Delphine Hermance Maxime PARENT
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
Safran Aircraft Engines 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 Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP3797213A1 publication Critical patent/EP3797213A1/en
Application granted granted Critical
Publication of EP3797213B1 publication Critical patent/EP3797213B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/127Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with a deformable or crushable structure, e.g. honeycomb
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00Geometry
    • F05D2250/10Two-dimensional
    • F05D2250/18Two-dimensional patterned
    • F05D2250/182Two-dimensional patterned crenellated, notched
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00Geometry
    • F05D2250/10Two-dimensional
    • F05D2250/18Two-dimensional patterned
    • F05D2250/183Two-dimensional patterned zigzag
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00Geometry
    • F05D2250/20Three-dimensional
    • F05D2250/28Three-dimensional patterned
    • F05D2250/283Three-dimensional patterned honeycomb
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00Function
    • F05D2260/30Retaining components in desired mutual position
    • F05D2260/36Retaining components in desired mutual position by a form fit connection, e.g. by interlocking

Definitions

  • the invention relates to an angular sector of a turbomachine vane, in particular an angular sector of a vane such as a rectifier equipping a compressor or such as a distributor equipping a turbine of the turbomachine.
  • the gas turbine engines comprise, in known manner, fixed internal blade crowns, which are mounted in external casings of a primary flow stream of the engine and which are interposed axially between mobile compressor blade wheels or between mobile turbine blade wheels of these engines.
  • Each fixed rotor ring is mounted with a dynamic seal around a compressor or turbine rotor.
  • each ring of fixed blades has internally a block of abradable material which is intended to cooperate with wiper seals integral in rotation of the associated compressor rotor or turbine to allow to ensure gas tightness.
  • Part of the gas is nevertheless likely to creep between the fixed blades and the moving blades of the compressor or turbine rotors, in the opposite direction of the main flow circulating in the primary flow vein.
  • Fixed internal blade crowns are rectifiers when interposed between compressor wheels, or constitute distributors when interposed between turbine wheels.
  • the fixed blade crowns are often made in the form of an assembly of angular sectors which are juxtaposed with each other. next to the others until forming an entire crown of fixed blades. These crowns thus reveal an inter-sector clearance that allows for recirculation passages for gases, no longer around the feet of the angular sectors, but between them.
  • the difficulty in ensuring a satisfactory level of sealing lies in the fact that the angular sectors of the crown move because of the mechanical and thermal deformations occurring during the operation of the engine.
  • the clearance between the sectors and the leakage rate vary during the operation of the engine.
  • the hot play during operation of the engine must also never be zero because contact between the platforms of the sectors may cause ovalization of the casing which is external to the fixed blade and / or matting of the surfaces in contact, this which could increase drastically the stresses exerted on the fixed blade, with the consequence in particular a postponement of these constraints on the outer casing of the engine which receives the fixed blade.
  • a postponement of these constraints may have the consequence of causing an ovalization of the outer casing and of significantly modifying the radial clearances between this casing and the neighboring mobile blades, with a very negative impact for the engine in terms of service life.
  • the sealing between two adjacent adjacent fixed crown crown sectors is ensured by tongue-and-groove sealing systems interposed between these sectors in order to limit leaks between sectors.
  • These sealing systems can be used to seal fixed rotor crown sectors placed in the primary flow vein, and also, in the case of a double-flow motor, to seal sectors. fixed crown crown placed in the vein of secondary flow.
  • tabs are housed between two adjacent sectors in housings that have been machined in the sectors.
  • the tabs make it possible to hinder the flow of gases passing through the inter-sector clearance.
  • an angular sector of the blade crown comprises, with respect to the axis of the ring gear, a radially outer platform substantially in the form of an angular section of a cylinder, a radially inner platform in the form of an angular section of a cylinder, at least two vanes extending between said platforms, a foot connected to the inner platform and at least one block of abradable honeycomb material extending inside the foot.
  • the tabs interposed between two sectors are embedded in the mass of the two adjacent feet of the two sectors and in housing vis-à-vis the inner and outer platforms adjacent to the two sectors.
  • the tabs can not be arranged over the entire radial thickness of the foot. As a result, there remains between the gaming sectors through which the gases can circulate.
  • the invention proposes to take advantage of the existing block of abradable material arranged inside the inner platform to provide a seal directly between transverse end walls of two adjacent angular sectors.
  • the invention proposes an angular sector of a fixed turbomachine rotor crown, in particular a stator or a distributor, said sector extending at a determined angle around an axis of the fixed crown of blades. and comprising, with respect to the axis of said fixed crown ring, a radially outer platform, a radially inner platform, at least two vanes which extend between said platforms, and at least one block of abradable nest material, bees that extend internally to the inner platform between transverse ends of the sector.
  • the block of abradable honeycomb material for example comprises a radially inner radial sealing face which is configured to cooperate with wipers of a labyrinth seal carried by a rotor of the turbomachine.
  • this angular sector is characterized in that the block of abradable material comprises at least one transverse end wall which is shaped according to a toothed profile comprising at least one radially extending tooth extending over a whole. radial thickness of said block.
  • the block of abradable material extends to the inner platform
  • each at least one tooth protrudes transversely from said block and is made of said abradable honeycomb material of said block,
  • the toothed profile has, in section in a plane perpendicular to the radial direction, a sawtooth shape
  • the toothed profile has, in section in a plane perpendicular to the radial direction, a crenellated form
  • the toothed profile comprises a single tooth shaped as a tenon
  • the single tooth formed as a tenon extends from one of the axial ends of the block
  • the abradable honeycomb material of the block comprises tubular cells oriented radially.
  • the invention also relates to an assembly of two adjacent angular sectors of the type described above, characterized in that said at least one transverse end wall formed according to a tooth profile of said adjacent angular sectors are facing each other, and in that said toothed profiles are complementary.
  • the invention relates to a fixed turbomachine rotor crown comprising a plurality of angular sectors of fixed rotor crown, characterized in that it comprises a predetermined number of sectors whose juxtaposition forms the entire crown of blading fixed, in that each angular sector comprises two opposite transverse end walls which are shaped according to toothed profiles each comprising at least one radially oriented tooth and in that each angular sector is assembled with each of the angular sectors which are adjacent in an assembly of the type described above.
  • FIG. 1 is a schematic sectional view of a turbomachine according to the state of the art
  • FIG. 2 is a sectional detail view of a turbine of the turbomachine of FIG. 1,
  • FIG. 3 is a sectional detail view of a compressor of the turbomachine of FIG. 1,
  • FIG. 4 is a perspective view of an assembly of angular sectors of vane according to the invention.
  • FIG. 5A is a sectional view of a crown crown sector according to the state of the art
  • FIG. 5B is a sectional view of a sector of a blade crown according to the invention.
  • FIG. 6 is a diagrammatic sectional view of a first tooth profile of a block of abradable material of a sector of a crown of blading according to the invention
  • FIG. 7 is a diagrammatic cross-sectional view of a second tooth profile of a block of abradable material of a crown crown sector according to the invention.
  • FIG. 8 is a diagrammatic sectional view of a third tooth profile of a block of abradable material of a sector of a crown of blading according to the invention.
  • FIG. 9 is a schematic sectional view of a fourth tooth profile of a block of abradable material of a blade crown sector according to the invention.
  • axial direction By axial direction, will be designated by extension any direction parallel to an axis A of a turbomachine, and by radial direction any direction perpendicular and extending radially relative to the axial direction.
  • FIG. 1 shows a turbomachine 10 of axis A of the double flow type.
  • a turbomachine 10 here a turbojet engine 10
  • LP low pressure compressor
  • HP high pressure compressor
  • HP high pressure turbine
  • LP low pressure turbine
  • exhaust nozzle 24 The rotor of the HP compressor 16 and the rotor of the HP turbine 20 are connected by an HP high pressure shaft 26 and form with it a high pressure body.
  • the rotor of the LP compressor 14 and the rotor of the LP low pressure turbine 22 are connected by an LP shaft 28 and form with it a low pressure body.
  • the high and low pressure bodies are traversed by a primary air flow "P” and the fan 12 produces a secondary air flow “S” which circulates in the turbojet engine 10, between a casing 11 and an outer casing 13 of the turbojet engine. in a cold flow channel 15.
  • the gases from the primary flow "P” are mixed with the secondary flow "S” to produce a propulsive force, the secondary flow "S” providing the majority here of the thrust.
  • the compressors BP 14 and HP 16 and the turbines HP 20 and BP 22 each respectively comprise several stages of compressor or turbine.
  • the LP turbine 22 comprises several turbine blades 22a, 22b, 22c, 22d, 22e of which the vanes are carried by associated ferrules 30a, 30b, 30c, 30d, 30e which are assembled to one another by bolts 36.
  • the LP turbine 22 further comprises fixed rotor crowns 32a, 32b, 32c, 32d of a diffuser 32 which are interposed between the turbine blades 22a, 22b, 22c, 22d, 22e.
  • Each ring of fixed vanes 32a, 32b, 32c, 32d of diffuser is formed of an assembly of sectors 34a, 34b, 34c, 34d fixed crown of rings, assembled around the axis A of the turbomachine 360 ° so as to form a fixed rotor ring 32a, 32b, 32c, 32d complete about the axis A of the turbomachine.
  • the HP compressor 16 of the turbomachine 10 may comprise a series of wheels 22a, 22b of mobile compressor blades between which are interwoven crowns 32a of fixed blades of rectifier which are themselves made in the form of an assembly of angular sectors 34a of fixed blade crowns. It will therefore be understood that the invention applies to any assembly of angular sectors 34a of fixed rotor crown 32a, whether angular sectors 34a of a rectifier for a compressor or angular sectors 34a d a diffuser for a turbine.
  • a fixed compressor crown 32a consists of an assembly of angular crown sectors 34a. It can be seen that each ring of fixed blades, and in particular the ring gear 32a, is placed in the primary flow stream P forming a clearance with the adjacent compressor wheels 22a and 22b, and in particular with ferrules 30a and 30b of these wheels 22a, 22b. Part of the pressurized gases of the primary flow P, which flows from upstream to downstream, tends to creep between the shells 30a and 30b and the angular sector 34a to recirculate from downstream to upstream according to a recirculation flow rc, represented by the arrows of Figure 3, which tends to bypass the angular sector 34a.
  • this recirculation flow rc is particularly penalizing.
  • the recirculation flow rc tends to reduce the performance of the compressor, or similarly when it is a turbine, the performance of said turbine. This is the reason why current designs tend to minimize this recirculation flow rc by equipping the angular sector 34a with sealing means with the ferrule it surrounds.
  • each sector 34a extends at a determined angle around the axis of the ring gear 32a, which corresponds to the axis A of the turbomachine previously illustrated in FIG.
  • each sector 34a comprises, relative to the axis A of the ring 32a, a radially outer platform 38a, a radially inner platform 40a, at least two blades 42a which extend between said platforms 38a, 40a, a foot 43a which extends radially inwardly from the inner platform 40a and at least one block 44a of abradable honeycomb material which therefore therefore extends internally also to the inner platform 40a between ends transverse (not shown) of the angular sector 34a.
  • a radially inner radial sealing face 46a is configured to cooperate with wipers 48a of a labyrinth seal 50a carried by a rotor of the turbomachine, here the ferrule 30a.
  • This configuration substantially reduces the intensity of recirculation flow rc flowing between sector 34a and ferrule 30a. However, it has no influence on the recirculation flow between two adjacent sectors 34a.
  • the sealing between adjacent sectors 34a is achieved by means of tabs (not shown) which are received in housings opposite the adjacent sectors 34a and which are arranged between these sectors 34a to form a barrier to the recirculation flow between sectors 34a.
  • This configuration is particularly expensive because it requires making housing for the tabs in particular in the feet 43a and because it requires special mounting precautions, particularly with regard to sectors that are intended to close the entire blade during of its assembly.
  • the invention proposes to simplify the sealing between the sectors 34a by taking advantage of the block 44a of abradable material already present radially inside the inner platform 40a so as to ensure a seal directly between transverse end walls of two adjacent angular sectors.
  • the invention proposes an angular sector 34a of a fixed turbomachine rotor crown of the type described above, characterized in that the block 44a of abradable material comprises at least one wall transverse end 52a which is shaped according to a toothed profile 54a1, 54a2 having at least one radially oriented tooth 56a1, 56a2 R, said at least one radial tooth 56a1, 56a2 extending along an entire radial thickness of said block 44a.
  • Figure 4 shows an assembly of two angular sectors 34a fixed crown of blades.
  • Each of these two fixed rotor crown angular sectors 34a has a transverse end wall 52a which faces the transverse end wall 52a of the other fixed crown crown sector 34a.
  • the block 44a of one of the sectors 34a comprises a toothed profile 54a1 comprising at least one tooth 56a1 and the block 44a of the other of the sectors 34a comprises a toothed profile 54a2, complementary to the tooth profile 54a1, which comprises at least a tooth 56a1. Sealing is therefore provided in the opposite direction of the primary flow P by the cooperation of the transverse end walls 52a and their toothed profiles 54a1 and 54a2 complementary.
  • the fixed rotor crown 32a comprises a predetermined number of crown sectors 34a whose juxtaposition forms the entirety of the fixed crown 32a and comprises at least two of these angular crown sectors 34a having toothed profiles. 54a1, 54a2. It will be understood that, of course, all crown sectors 34a preferably comprise toothed profiles.
  • each angular sector 34a is assembled with each of the angular sectors 34a which are adjacent to it in an assembly of the type described above, and each block 44a has at its two ends opposite transverse end walls 52a which are shaped according to toothed profiles. 54a1, 54a2 intended to cooperate with the toothed profiles 54a1, 54a2 with radially oriented teeth of the adjacent blocks 44a.
  • the block of abradable material 44a of the sector 34a extends to the inner platform 40a.
  • This configuration has been shown in Figure 5B.
  • the foot 43a has been removed and the block 44a of honeycomb material has been extended radially to the inner platform 40a so as to give a maximum height to the block 44a of honeycomb material, and in doing so, to give it maximum sealing.
  • this configuration makes it possible to dispense with the installation of a conventional sealing system with tabs arranged on the foot 43a.
  • each inner platform 40a has an end edge 58a which is shaped according to a toothed profile 60a1, 60a2 which is superimposed on the toothed profile 54a1, 54a2 of the block of honeycomb material 44a corresponding.
  • toothed profiles 60a1, 60a2 are also complementary to one another.
  • the configuration is not limiting of the invention, and the end edges 58a of the inner platforms 40a could be rectilinear.
  • each tooth 56a1 or 56a2 of each block 44a can be made in different ways.
  • the teeth 56a1 or 56a2 could be reported to the block 44a, provided they protrude from the block 44a.
  • each tooth 56a1 or 56a2 is preferably made directly in the abradable honeycomb material of the block 44a.
  • the toothed profile 54a1, 54a2 of the block of honeycomb material 44a can take different configurations depending on the desired seal.
  • the number of teeth 56a1 or 56a2 will result from a compromise between the efficiency of reducing the flow rate of the recirculation flow rc and the cost of obtaining the ring 32a formed of the angular sectors 34a, this cost including the realization of these sectors 34a and their assembly.
  • the toothed profile 54a1, 54a2 may have, in section in a plane perpendicular to a radial direction R, a crenellated shape, ie having substantially sectioned teeth. rectangular or square.
  • the toothed profile 54a1, 54a2 may have, in section in the plane perpendicular to the radial direction R, a sawtooth form.
  • the toothed profile 54a1, 54a2 of each sector 44a may comprise a tenon which is the only tooth 56a1, 56a2.
  • the single tooth shaped tooth 56a1, 56a2 extends from one of the axial ends 62a1 or 62a2 of the block 44a.
  • the abradable honeycomb material of the block 44a comprises tubular cells (not shown) which are oriented radially in the radial direction R. This configuration makes it possible to provide maximum resistance to the block of material 44a.
  • the honeycomb material of block 44a is obtained by an additive manufacturing process. This configuration allows the formation of regular cells and a regular conformation of toothed profiles 54a1, 54a2 without risk of deterioration as could risk causing a material removal process.
  • the invention therefore advantageously makes it possible to ensure the sealing between fixed rotor crown angular sectors 32a in a simple and effective manner, and to limit the flow rate of the recirculation flow rc between these angular sectors 32a, which makes it possible to significantly improve the performance of a compressor or a turbine equipped with such angular sectors of blade crown 32a.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention concerns an angular sector (34a) of a fixed blade ring of a turbomachine, in particular a stator or a guide vane assembly, said sector (34a) extending according to a predetermined angle around an axis of the fixed blade ring and comprising, relative to the axis of said fixed blade ring, a radially outer platform (38a), a radially inner platform (40a), at least two blades (42a) that extend between said platforms (38a, 40a), and at least one block of abradable honeycomb material (44a) that extends on the inside of the inner platform (38a) between transverse ends of the sector (34a), characterised in that the block (44a) of abradable material comprises at least one transverse end wall (52a) that is shaped according to a toothed profile (54a1, 54a2) comprising at least one radially oriented (R) tooth (56a1, 56a2) extending across an entire radial thickness of said block (44a). Abstract drawing: Figure 4. .

Description

SECTEUR ANGULAIRE D'AUBAGE DE TURBOMACHINE A  ANGULAR TURBOMACHINE A TURBINE CURING SECTOR
ETANCHEITE PERFECTIONNEE  PERFECTED SEALING
L'invention concerne un secteur angulaire d'un aubage de turbomachine, notamment un secteur angulaire d'un aubage tel qu’un redresseur équipant un compresseur ou tel qu’un distributeur équipant une turbine de la turbomachine. The invention relates to an angular sector of a turbomachine vane, in particular an angular sector of a vane such as a rectifier equipping a compressor or such as a distributor equipping a turbine of the turbomachine.
ETAT DE LA TECHNIQUE ANTERIEURE STATE OF THE PRIOR ART
Les moteurs à turbine à gaz comportent de manière connue des couronnes d’aubages internes fixes, qui sont montées dans des carters externes d'une veine de flux primaire du moteur et qui sont intercalées axialement entre des roues d’aubages mobiles de compresseur ou entre des roues d’aubages mobiles de turbine de ces moteurs. Chaque couronne d’aubages fixes est montée avec une étanchéité dynamique autour d’un rotor de compresseur ou de turbine. A cet effet, chaque couronne d’aubages fixes comporte intérieurement un bloc de matériau abradable qui est destiné à coopérer avec des joints à léchettes solidaires en rotation du rotor de compresseur ou de turbine associé pour permettre d’assurer une étanchéité aux gaz. The gas turbine engines comprise, in known manner, fixed internal blade crowns, which are mounted in external casings of a primary flow stream of the engine and which are interposed axially between mobile compressor blade wheels or between mobile turbine blade wheels of these engines. Each fixed rotor ring is mounted with a dynamic seal around a compressor or turbine rotor. For this purpose, each ring of fixed blades has internally a block of abradable material which is intended to cooperate with wiper seals integral in rotation of the associated compressor rotor or turbine to allow to ensure gas tightness.
Une partie des gaz est néanmoins susceptible de s'insinuer entre les aubages fixes et les aubages mobiles des rotors de compresseur ou de turbine, en sens inverse du flux principal circulant dans la veine de flux primaire.  Part of the gas is nevertheless likely to creep between the fixed blades and the moving blades of the compressor or turbine rotors, in the opposite direction of the main flow circulating in the primary flow vein.
Les couronnes d’aubages internes fixes constituent des redresseurs lorsqu'elles sont intercalées entre des roues de compresseur, ou constituent des distributeurs lorsqu'elles sont intercalées entre des roues de turbine.  Fixed internal blade crowns are rectifiers when interposed between compressor wheels, or constitute distributors when interposed between turbine wheels.
Dans le but de faciliter leur montage et de réduire leur coût de fabrication, les couronnes d’aubages fixes sont souvent réalisées sous la forme d'un assemblage de secteurs angulaires qui sont juxtaposés les uns à côté des autres jusqu'à former une couronne entière d’aubages fixes. Ces couronnes laissent ainsi apparaître un jeu inter-secteurs qui laisse subsister des passages de recirculation pour les gaz, non plus autour des pieds des secteurs angulaires, mais entre ceux-ci. In order to facilitate their assembly and to reduce their manufacturing cost, the fixed blade crowns are often made in the form of an assembly of angular sectors which are juxtaposed with each other. next to the others until forming an entire crown of fixed blades. These crowns thus reveal an inter-sector clearance that allows for recirculation passages for gases, no longer around the feet of the angular sectors, but between them.
En effet, conventionnellement, une partie des gaz qui traversent d'amont en aval les aubages fixes a tendance à recirculer de l'aval vers l'amont à travers l'étanchéité qui est réalisée entre le bloc de matériau abradable et le joint à léchettes selon un débit de fuite que l'on cherche à maintenir aussi minimal que possible, car il affecte les performances du compresseur ou de la turbine correspondante. Une autre partie des gaz qui traverse d'amont en aval ces aubages a tendance à recirculer de l'aval vers l'amont en s'insinuant entre les secteurs en passant par le jeu entre les secteurs, aussi appelé jeu inter-secteurs.  Indeed, conventionally, a portion of the gases that flow from the upstream to the downstream fixed blades tends to recirculate from downstream to upstream through the seal that is formed between the block of abradable material and the gasket according to a leakage flow that is sought to maintain as minimal as possible, because it affects the performance of the compressor or the corresponding turbine. Another portion of the gas that flows upstream from downstream of these blades tends to recirculate from downstream to upstream by creeping between sectors through the interplay between sectors, also called inter-sector play.
La difficulté pour assurer un niveau satisfaisant d’étanchéité réside dans le fait que les secteurs angulaires de couronne se déplacent du fait des déformations mécaniques et thermiques survenant lors du fonctionnement du moteur. Ainsi, le jeu entre les secteurs et le débit de fuite varient au cours du fonctionnement du moteur. Le jeu à chaud lors du fonctionnement du moteur ne doit par ailleurs jamais être nul car un contact entre les plateformes des secteurs risquerait de provoquer une ovalisation du carter qui est extérieur à l'aubage fixe et/ou un matage des surfaces en contact, ce qui risquerait d'augmenter de manière drastique les contraintes s'exerçant sur l'aubage fixe, avec notamment pour conséquence un report de ces contraintes sur le carter extérieur du moteur qui reçoit l'aubage fixe.  The difficulty in ensuring a satisfactory level of sealing lies in the fact that the angular sectors of the crown move because of the mechanical and thermal deformations occurring during the operation of the engine. Thus, the clearance between the sectors and the leakage rate vary during the operation of the engine. The hot play during operation of the engine must also never be zero because contact between the platforms of the sectors may cause ovalization of the casing which is external to the fixed blade and / or matting of the surfaces in contact, this which could increase drastically the stresses exerted on the fixed blade, with the consequence in particular a postponement of these constraints on the outer casing of the engine which receives the fixed blade.
Un report de ces contraintes peut avoir pour conséquence de causer une ovalisation du carter extérieur et de modifier de manière significative les jeux radiaux entre ce carter et les aubages mobiles voisins, avec un impact très négatif pour le moteur en terme de durée de vie.  A postponement of these constraints may have the consequence of causing an ovalization of the outer casing and of significantly modifying the radial clearances between this casing and the neighboring mobile blades, with a very negative impact for the engine in terms of service life.
Conventionnellement, l'étanchéité entre deux secteurs angulaires de couronne d'aubages fixes immédiatement voisins est assurée par des systèmes d’étanchéité à languettes interposés entre ces secteurs afin de limiter les fuites entre secteurs. Ces systèmes d'étanchéité peuvent être utilisés pour assurer l'étanchéité de secteurs de couronne d'aubages fixes placés dans la veine de flux primaire, et aussi, dans le cas d'un moteur à double flux, pour assurer l'étanchéité de secteurs de couronne d'aubages fixes placés dans la veine de flux secondaire. Conventionally, the sealing between two adjacent adjacent fixed crown crown sectors is ensured by tongue-and-groove sealing systems interposed between these sectors in order to limit leaks between sectors. These sealing systems can be used to seal fixed rotor crown sectors placed in the primary flow vein, and also, in the case of a double-flow motor, to seal sectors. fixed crown crown placed in the vein of secondary flow.
Selon cette technologie, des languettes sont logées entre deux secteurs adjacents dans des logements qui ont été usinés dans les secteurs. Les languettes permettent de faire obstacle à l’écoulement des gaz passant par le jeu inter-secteurs.  According to this technology, tabs are housed between two adjacent sectors in housings that have been machined in the sectors. The tabs make it possible to hinder the flow of gases passing through the inter-sector clearance.
Conventionnellement, un secteur angulaire de couronne d'aubages comporte, par rapport à l'axe de la couronne, une plateforme radialement extérieure sensiblement en forme de tronçon angulaire de cylindre, une plateforme radialement intérieure en forme de tronçon angulaire de cylindre, au moins deux aubes qui s'étendent entre lesdites plateformes, un pied lié à la plateforme intérieure et au moins un bloc de matériau abradable en nid d'abeilles qui s'étend intérieurement au pied. Les languettes interposées entre deux secteurs sont enchâssées dans la masse des deux pieds adjacents des deux secteurs et dans des logements en vis-à-vis des plateformes intérieures et extérieures adjacentes des deux secteurs.  Conventionally, an angular sector of the blade crown comprises, with respect to the axis of the ring gear, a radially outer platform substantially in the form of an angular section of a cylinder, a radially inner platform in the form of an angular section of a cylinder, at least two vanes extending between said platforms, a foot connected to the inner platform and at least one block of abradable honeycomb material extending inside the foot. The tabs interposed between two sectors are embedded in the mass of the two adjacent feet of the two sectors and in housing vis-à-vis the inner and outer platforms adjacent to the two sectors.
Ces languettes sont toutefois peu aisées à monter. En outre, elles nécessitent la réalisation de logements dans les secteurs angulaires d'aubages fixes, qui sont d'un coût de fabrication élevé.  These tabs are however easy to assemble. In addition, they require the production of housing in the angular sectors of fixed blades, which are of a high manufacturing cost.
En ce qui concerne l'étanchéité réalisée intérieurement à la plateforme intérieure, les languettes ne peuvent de plus pas être agencées suivant toute l'épaisseur radiale du pied. Par conséquent, il subsiste entre les secteurs des jeux par lesquels les gaz peuvent circuler.  Regarding the seal made internally to the inner platform, the tabs can not be arranged over the entire radial thickness of the foot. As a result, there remains between the gaming sectors through which the gases can circulate.
Il existe donc un besoin pour une technologie d'étanchéité alternative permettant de se dispenser de telles languettes et d'améliorer l'étanchéité entre les secteurs d'aubage fixe. Le document FR-2.552.159-A1 décrit une technologie dans laquelle des bords des plateformes intérieures sont conformés selon un profil en Z. Cette configuration améliore l'efficacité de l'étanchéité mais est limitée aux plateformes et ne s'applique qu'à un distributeur dont le bloc de matériau abradable n'est pas sectorisé. There is therefore a need for an alternative sealing technology to dispense with such tongues and improve the seal between the sectors of fixed blade. The document FR-2.552.159-A1 describes a technology in which edges of the inner platforms are shaped according to a Z-shaped profile. This configuration improves the effectiveness of the sealing but is limited to the platforms and applies only to a distributor whose block of abradable material is not sectorized.
EXPOSÉ DE L'INVENTION STATEMENT OF THE INVENTION
L'invention propose de tirer parti du bloc de matériau abradable existant agencé à l'intérieur de la plateforme intérieure pour assurer une étanchéité directement entre des parois d'extrémités transversales de deux secteurs angulaires adjacents. The invention proposes to take advantage of the existing block of abradable material arranged inside the inner platform to provide a seal directly between transverse end walls of two adjacent angular sectors.
Dans ce but, l'invention propose un secteur angulaire d'une couronne d’aubages fixes de turbomachine, notamment de redresseur ou de distributeur, ledit secteur s'étendant suivant un angle déterminé autour d'un axe de la couronne d’aubages fixes et comportant, par rapport à l'axe de ladite couronne d’aubages fixes, une plateforme radialement extérieure, une plateforme radialement intérieure, au moins deux aubes qui s'étendent entre lesdites plateformes, et au moins un bloc de matériau abradable en nid d'abeilles qui s'étend intérieurement à la plateforme intérieure entre des extrémités transversales du secteur.  For this purpose, the invention proposes an angular sector of a fixed turbomachine rotor crown, in particular a stator or a distributor, said sector extending at a determined angle around an axis of the fixed crown of blades. and comprising, with respect to the axis of said fixed crown ring, a radially outer platform, a radially inner platform, at least two vanes which extend between said platforms, and at least one block of abradable nest material, bees that extend internally to the inner platform between transverse ends of the sector.
Le bloc de matériau abradable en nid d'abeilles comporte par exemple une face radialement intérieure d'étanchéité radiale qui est configurée pour coopérer avec des léchettes d'un joint à labyrinthe porté par un rotor de la turbomachine.  The block of abradable honeycomb material for example comprises a radially inner radial sealing face which is configured to cooperate with wipers of a labyrinth seal carried by a rotor of the turbomachine.
Conformément à l’invention, ce secteur angulaire est caractérisé en ce que le bloc de matériau abradable comporte au moins une paroi d'extrémité transversale qui est conformée selon un profil denté comportant au moins une dent d'orientation radiale s'étendant suivant toute une épaisseur radiale dudit bloc.  According to the invention, this angular sector is characterized in that the block of abradable material comprises at least one transverse end wall which is shaped according to a toothed profile comprising at least one radially extending tooth extending over a whole. radial thickness of said block.
Selon d'autres caractéristiques du secteur angulaire : - le bloc de matériau abradable s'étend jusqu'à la plateforme intérieure, According to other characteristics of the angular sector: the block of abradable material extends to the inner platform,
- chaque au moins une dent fait saillie transversalement à partir dudit bloc et est réalisée dans ledit matériau abradable en nid d'abeilles dudit bloc,  each at least one tooth protrudes transversely from said block and is made of said abradable honeycomb material of said block,
- le profil denté présente, en section dans un plan perpendiculaire à la direction radiale, une forme en dents de scie,  - The toothed profile has, in section in a plane perpendicular to the radial direction, a sawtooth shape,
- le profil denté présente, en section dans un plan perpendiculaire à la direction radiale, une forme crénelée,  the toothed profile has, in section in a plane perpendicular to the radial direction, a crenellated form,
- le profil denté comporte une unique dent conformée en tenon, the toothed profile comprises a single tooth shaped as a tenon,
- l'unique dent conformée en tenon s'étend à partir d'une des extrémités axiales du bloc, the single tooth formed as a tenon extends from one of the axial ends of the block,
- le matériau abradable en nid d'abeilles du bloc comporte des alvéoles tubulaires orientées radialement.  the abradable honeycomb material of the block comprises tubular cells oriented radially.
L'invention concerne aussi un assemblage de deux secteurs angulaires adjacents du type décrit précédemment, caractérisé en ce que lesdites au moins une paroi d'extrémité transversale conformée selon un profil denté desdits secteurs angulaires adjacents sont tournées l'une vers l'autre, et en ce que lesdits profils dentés sont complémentaires.  The invention also relates to an assembly of two adjacent angular sectors of the type described above, characterized in that said at least one transverse end wall formed according to a tooth profile of said adjacent angular sectors are facing each other, and in that said toothed profiles are complementary.
L'invention concerne enfin une couronne d’aubages fixes de turbomachine comportant une pluralité de secteurs angulaires de couronne d’aubages fixes, caractérisé en ce qu'elle comporte un nombre déterminé de secteurs dont la juxtaposition forme la totalité de la couronne d’aubages fixes, en ce que chaque secteur angulaire comporte deux parois d'extrémités transversales opposées qui sont conformées selon des profils dentés comportant chacun au moins une dent d'orientation radiale et en ce que chaque secteur angulaire est assemblé avec chacun des secteurs angulaires qui lui sont adjacents dans un assemblage du type décrit précédemment. DESCRIPTION DES FIGURES Finally, the invention relates to a fixed turbomachine rotor crown comprising a plurality of angular sectors of fixed rotor crown, characterized in that it comprises a predetermined number of sectors whose juxtaposition forms the entire crown of blading fixed, in that each angular sector comprises two opposite transverse end walls which are shaped according to toothed profiles each comprising at least one radially oriented tooth and in that each angular sector is assembled with each of the angular sectors which are adjacent in an assembly of the type described above. DESCRIPTION OF THE FIGURES
L’invention sera mieux comprise et d’autres détails, caractéristiques et avantages de la présente invention apparaîtront plus clairement à la lecture de la description qui suit faite à titre d’exemple non limitatif et en référence aux dessins annexés, dans lesquels : The invention will be better understood and other details, characteristics and advantages of the present invention will appear more clearly on reading the following description given by way of nonlimiting example and with reference to the accompanying drawings, in which:
- la figure 1 est une vue schématique en coupe d'une turbomachine selon l'état de la technique,  FIG. 1 is a schematic sectional view of a turbomachine according to the state of the art,
- la figure 2 est une vue de détail en coupe d'une turbine de la turbomachine de la figure 1 ,  FIG. 2 is a sectional detail view of a turbine of the turbomachine of FIG. 1,
- la figure 3 est une vue en de détail en coupe d'un compresseur de la turbomachine de la figure 1 ,  FIG. 3 is a sectional detail view of a compressor of the turbomachine of FIG. 1,
- la figure 4 est une vue en perspective d'un assemblage de secteurs angulaires d'aubage selon l'invention,  FIG. 4 is a perspective view of an assembly of angular sectors of vane according to the invention,
- la figure 5A est une vue en coupe d'un secteur de couronne d'aubages selon l'état de la technique,  FIG. 5A is a sectional view of a crown crown sector according to the state of the art,
- la figure 5B est une vue en coupe d'un secteur de couronne d'aubages selon l'invention,  FIG. 5B is a sectional view of a sector of a blade crown according to the invention,
- la figure 6 est une vue schématique en coupe d'un premier profil denté d'un bloc de matériau abradable d'un secteur de couronne d'aubages selon l'invention,  FIG. 6 is a diagrammatic sectional view of a first tooth profile of a block of abradable material of a sector of a crown of blading according to the invention,
- la figure 7 est une vue schématique en coupe d'un deuxième profil denté d'un bloc de matériau abradable d'un secteur de couronne d'aubages selon l'invention,  FIG. 7 is a diagrammatic cross-sectional view of a second tooth profile of a block of abradable material of a crown crown sector according to the invention;
- la figure 8 est une vue schématique en coupe d'un troisième profil denté d'un bloc de matériau abradable d'un secteur de couronne d'aubages selon l'invention,  FIG. 8 is a diagrammatic sectional view of a third tooth profile of a block of abradable material of a sector of a crown of blading according to the invention,
- la figure 9 est une vue schématique en coupe d'un quatrième profil denté d'un bloc de matériau abradable d'un secteur de couronne d'aubages selon l'invention. DESCRIPTION DETAILLEE - Figure 9 is a schematic sectional view of a fourth tooth profile of a block of abradable material of a blade crown sector according to the invention. DETAILED DESCRIPTION
Dans la description qui va suivre, des chiffres de référence identiques désignent des pièces identiques ou ayant des fonctions similaires. In the following description, like reference numerals designate like parts or having similar functions.
Par direction axiale, on désignera par extension toute direction parallèle à un axe A d'une turbomachine, et par direction radiale toute direction perpendiculaire et s'étendant radialement par rapport à le direction axiale.  By axial direction, will be designated by extension any direction parallel to an axis A of a turbomachine, and by radial direction any direction perpendicular and extending radially relative to the axial direction.
On a représenté à la figure 1 une turbomachine 10 d'axe A du type à double flux. Une telle turbomachine 10, ici un turboréacteur 10, comporte de manière connue une soufflante 12, un compresseur basse pression (BP) 14, un compresseur haute pression (HP) 16, une chambre de combustion 18, une turbine haute pression (HP) 20, une turbine basse pression (BP) 22 et une tuyère d'échappement 24. Le rotor du compresseur HP 16 et le rotor de la turbine HP 20 sont reliés par un arbre haute pression HP 26 et forment avec lui un corps haute pression. Le rotor du compresseur BP 14 et le rotor de la turbine basse pression BP 22 sont reliés par un arbre BP 28 et forment avec lui un corps basse pression.  FIG. 1 shows a turbomachine 10 of axis A of the double flow type. Such a turbomachine 10, here a turbojet engine 10, comprises in known manner a fan 12, a low pressure compressor (LP) 14, a high pressure compressor (HP) 16, a combustion chamber 18, a high pressure turbine (HP) 20 , a low pressure turbine (LP) 22 and an exhaust nozzle 24. The rotor of the HP compressor 16 and the rotor of the HP turbine 20 are connected by an HP high pressure shaft 26 and form with it a high pressure body. The rotor of the LP compressor 14 and the rotor of the LP low pressure turbine 22 are connected by an LP shaft 28 and form with it a low pressure body.
Les corps haute et basse pression sont traversés par un flux d'air primaire "P" et la soufflante 12 produit un flux d'air secondaire "S" qui circule dans le turboréacteur 10, entre un carter 11 et une enveloppe externe 13 du turboréacteur, dans un canal de flux froid 15. En sortie de la tuyère 24, les gaz issus du flux primaire "P" sont mélangés au flux secondaire "S" pour produire une force de propulsion, le flux secondaire "S" fournissant ici la majorité de la poussée.  The high and low pressure bodies are traversed by a primary air flow "P" and the fan 12 produces a secondary air flow "S" which circulates in the turbojet engine 10, between a casing 11 and an outer casing 13 of the turbojet engine. in a cold flow channel 15. At the outlet of the nozzle 24, the gases from the primary flow "P" are mixed with the secondary flow "S" to produce a propulsive force, the secondary flow "S" providing the majority here of the thrust.
Les compresseurs BP 14 et HP 16 et les turbines HP 20 et BP 22 comportent chacun respectivement plusieurs étages de compresseur ou de turbine. Comme l'illustre par exemple la figure 2, la turbine BP 22 comporte plusieurs roues d'aubages mobiles 22a, 22b, 22c, 22d, 22e de turbine dont les aubages sont portés par des viroles 30a, 30b, 30c, 30d, 30e associées qui sont assemblées les unes aux autres par des boulons 36. The compressors BP 14 and HP 16 and the turbines HP 20 and BP 22 each respectively comprise several stages of compressor or turbine. As illustrated for example in FIG. 2, the LP turbine 22 comprises several turbine blades 22a, 22b, 22c, 22d, 22e of which the vanes are carried by associated ferrules 30a, 30b, 30c, 30d, 30e which are assembled to one another by bolts 36.
La turbine BP 22 comporte par ailleurs des couronnes d’aubages fixes 32a, 32b, 32c, 32d d'un diffuseur 32 qui sont intercalées entre les roues d'aubages mobiles 22a, 22b, 22c, 22d, 22e de turbine.  The LP turbine 22 further comprises fixed rotor crowns 32a, 32b, 32c, 32d of a diffuser 32 which are interposed between the turbine blades 22a, 22b, 22c, 22d, 22e.
Chaque couronne d’aubages fixes 32a, 32b, 32c, 32d de diffuseur est formée d'un assemblage de secteurs 34a, 34b, 34c, 34d de couronne d'aubages fixes, assemblés autour de l'axe A de la turbomachine sur 360° de manière à constituer une couronne d’aubages fixes 32a, 32b, 32c, 32d complète autour de l'axe A de la turbomachine.  Each ring of fixed vanes 32a, 32b, 32c, 32d of diffuser is formed of an assembly of sectors 34a, 34b, 34c, 34d fixed crown of rings, assembled around the axis A of the turbomachine 360 ° so as to form a fixed rotor ring 32a, 32b, 32c, 32d complete about the axis A of the turbomachine.
De la même manière, comme l’illustrent les figures 3 à 5B, le compresseur HP 16 de la turbomachine 10 peut comporter une série de roues 22a, 22b d’aubages mobiles de compresseur entre lesquelles sont intercalées des couronnes 32a d’aubages fixes de redresseur qui sont elles-mêmes réalisées sous la forme d’un assemblage de secteurs angulaires 34a de couronnes d’aubages fixes. Il sera donc compris que l’invention s’applique à tout assemblage de secteurs angulaires 34a de couronne d’aubages fixes 32a, qu’il s’agisse de secteurs angulaires 34a d’un redresseur destiné à un compresseur ou de secteurs angulaires 34a d’un diffuseur destiné à une turbine.  In the same way, as illustrated in FIGS. 3 to 5B, the HP compressor 16 of the turbomachine 10 may comprise a series of wheels 22a, 22b of mobile compressor blades between which are interwoven crowns 32a of fixed blades of rectifier which are themselves made in the form of an assembly of angular sectors 34a of fixed blade crowns. It will therefore be understood that the invention applies to any assembly of angular sectors 34a of fixed rotor crown 32a, whether angular sectors 34a of a rectifier for a compressor or angular sectors 34a d a diffuser for a turbine.
Comme l'illustre plus en détail la figure 3, une couronne d’aubages fixes 32a de compresseur est constitué d’un assemblage de secteurs angulaires 34a de couronne d’aubages. On voit que chaque couronne d’aubages fixes, et en particulier la couronne 32a, est placée dans la veine de flux primaire P en formant un jeu avec les roues adjacentes de compresseur 22a et 22b, et en particulier avec des viroles 30a et 30b de ces roues 22a, 22b. Une partie des gaz sous pression du flux primaire P, qui circule de l’amont vers l’aval, tend à s’insinuer entre les viroles 30a et 30b et le secteur angulaire 34a pour recirculer de l’aval vers l’amont selon un flux de recirculation rc, représenté par les flèches de la figure 3, qui tend à contourner le secteur angulaire 34a. L’existence de ce flux de recirculation rc est particulièrement pénalisante. Le flux de recirculation rc tend à diminuer les performances du compresseur, ou similairement lorsqu’il s’agit d’une turbine, les performances de ladite turbine. C’est la raison pour laquelle les conceptions actuelles tendent à minimiser ce flux de recirculation rc en équipant le secteur angulaire 34a de moyens d’étanchéité avec la virole qu’il entoure. As illustrated in more detail in FIG. 3, a fixed compressor crown 32a consists of an assembly of angular crown sectors 34a. It can be seen that each ring of fixed blades, and in particular the ring gear 32a, is placed in the primary flow stream P forming a clearance with the adjacent compressor wheels 22a and 22b, and in particular with ferrules 30a and 30b of these wheels 22a, 22b. Part of the pressurized gases of the primary flow P, which flows from upstream to downstream, tends to creep between the shells 30a and 30b and the angular sector 34a to recirculate from downstream to upstream according to a recirculation flow rc, represented by the arrows of Figure 3, which tends to bypass the angular sector 34a. The existence of this recirculation flow rc is particularly penalizing. The recirculation flow rc tends to reduce the performance of the compressor, or similarly when it is a turbine, the performance of said turbine. This is the reason why current designs tend to minimize this recirculation flow rc by equipping the angular sector 34a with sealing means with the ferrule it surrounds.
Comme l’illustre la figure 3, chaque secteur 34a s'étend suivant un angle déterminé autour de l’axe de la couronne 32a, qui correspond à l’axe A de la turbomachine précédemment illustré sur la figure 1.  As illustrated in FIG. 3, each sector 34a extends at a determined angle around the axis of the ring gear 32a, which corresponds to the axis A of the turbomachine previously illustrated in FIG.
Par "inférieur", on désignera tout positionnement proche de l'axe A selon la direction radiale alors que par "supérieur", on désignera tout positionnement plus éloigné de l'axe A selon la direction radiale que le positionnement inférieur. Enfin, par "transversal" on désignera tout plan ou toute surface comprenant l'axe A et parallèle à un plan de section d'un secteur 34.  By "lower", will be designated any positioning close to the axis A in the radial direction, while "higher" will be any positioning further from the axis A in the radial direction than the lower position. Finally, "transverse" means any plane or surface including the axis A and parallel to a section plane of a sector 34.
Conventionnellement, chaque secteur 34a comporte, par rapport à l'axe A de la couronne 32a, une plateforme 38a radialement extérieure, une plateforme 40a radialement intérieure, au moins deux aubes 42a qui s'étendent entre lesdites plateformes 38a, 40a, un pied 43a qui s’étend radialement vers l’intérieur à partir de la plate-forme intérieure 40a et au moins un bloc 44a de matériau abradable en nid d'abeilles qui s'étend donc par conséquent intérieurement lui aussi à la plateforme intérieure 40a entre des extrémités transversales (non représentées) du secteur angulaire 34a.  Conventionally, each sector 34a comprises, relative to the axis A of the ring 32a, a radially outer platform 38a, a radially inner platform 40a, at least two blades 42a which extend between said platforms 38a, 40a, a foot 43a which extends radially inwardly from the inner platform 40a and at least one block 44a of abradable honeycomb material which therefore therefore extends internally also to the inner platform 40a between ends transverse (not shown) of the angular sector 34a.
Une face radialement intérieure d'étanchéité radiale 46a est configurée pour coopérer avec des léchettes 48a d'un joint à labyrinthe 50a porté par un rotor de la turbomachine, ici la virole 30a.  A radially inner radial sealing face 46a is configured to cooperate with wipers 48a of a labyrinth seal 50a carried by a rotor of the turbomachine, here the ferrule 30a.
Cette configuration permet sensiblement de réduire l’intensité du flux de recirculation rc circulant entre le secteur 34a et la virole 30a. Toutefois elle n’a pas d’influence sur le flux de recirculation entre deux secteurs 34a adjacents. Conventionnellement, l’étanchéité entre des secteurs adjacents 34a est réalisée par l’intermédiaire de languettes (non représentées) qui sont reçues dans des logements en regard des secteurs adjacents 34a et qui sont agencés entre ces secteurs 34a pour former une barrière au flux de recirculation rc entre les secteurs 34a. Cette configuration est particulièrement coûteuse car elle nécessite de réaliser des logements pour les languettes notamment dans les pieds 43a et car elle impose des précautions de montage particulières, notamment en ce qui concerne les secteurs qui sont destinés à fermer l’ensemble de l’aubage lors de son montage. This configuration substantially reduces the intensity of recirculation flow rc flowing between sector 34a and ferrule 30a. However, it has no influence on the recirculation flow between two adjacent sectors 34a. Conventionally, the sealing between adjacent sectors 34a is achieved by means of tabs (not shown) which are received in housings opposite the adjacent sectors 34a and which are arranged between these sectors 34a to form a barrier to the recirculation flow between sectors 34a. This configuration is particularly expensive because it requires making housing for the tabs in particular in the feet 43a and because it requires special mounting precautions, particularly with regard to sectors that are intended to close the entire blade during of its assembly.
Comme l’illustre la figure 4, l'invention propose de simplifier l’étanchéité entre les secteurs 34a en tirant parti du bloc 44a de matériau abradable déjà présent radialement à l'intérieur de la plateforme intérieure 40a de manière à assurer une étanchéité directement entre des parois d'extrémités transversales de deux secteurs angulaires adjacents.  As illustrated in FIG. 4, the invention proposes to simplify the sealing between the sectors 34a by taking advantage of the block 44a of abradable material already present radially inside the inner platform 40a so as to ensure a seal directly between transverse end walls of two adjacent angular sectors.
Dans ce but, comme l’illustre la figure 4, l'invention propose un secteur angulaire 34a d'une couronne d’aubages fixes de turbomachine du type décrit précédemment, caractérisé en ce que le bloc 44a de matériau abradable comporte au moins une paroi d'extrémité transversale 52a qui est conformée selon un profil denté 54a1 , 54a2 comportant au moins une dent 56a1 , 56a2 d'orientation radiale R, ladite au moins une dent 56a1 , 56a2 radiale s'étendant suivant toute une épaisseur radiale dudit bloc 44a.  For this purpose, as illustrated in FIG. 4, the invention proposes an angular sector 34a of a fixed turbomachine rotor crown of the type described above, characterized in that the block 44a of abradable material comprises at least one wall transverse end 52a which is shaped according to a toothed profile 54a1, 54a2 having at least one radially oriented tooth 56a1, 56a2 R, said at least one radial tooth 56a1, 56a2 extending along an entire radial thickness of said block 44a.
Ainsi, la figure 4 représente un assemblage de deux secteurs angulaires 34a de couronne d’aubages fixes. Chacun de ces deux secteurs angulaires 34a de couronne d’aubages fixes comporte une paroi d’extrémité transversale 52a qui est tournée vers la paroi d’extrémité transversale 52a de l’autre secteur 34a de couronne d’aubages fixes.  Thus, Figure 4 shows an assembly of two angular sectors 34a fixed crown of blades. Each of these two fixed rotor crown angular sectors 34a has a transverse end wall 52a which faces the transverse end wall 52a of the other fixed crown crown sector 34a.
Comme l’illustre plus particulièrement la figure 6, le bloc 44a de l’un des secteurs 34a comporte un profil denté 54a1 comportant au moins une dent 56a1 et le bloc 44a de l’autre des secteurs 34a comporte un profil denté 54a2, complémentaire du profil denté 54a1 , qui comporte au moins une dent 56a1. L’étanchéité est donc assurée en sens inverse du flux primaire P par la coopération des parois d’extrémité transversale 52a et de leurs profils dentés 54a1 et 54a2 complémentaires. As is more particularly illustrated in FIG. 6, the block 44a of one of the sectors 34a comprises a toothed profile 54a1 comprising at least one tooth 56a1 and the block 44a of the other of the sectors 34a comprises a toothed profile 54a2, complementary to the tooth profile 54a1, which comprises at least a tooth 56a1. Sealing is therefore provided in the opposite direction of the primary flow P by the cooperation of the transverse end walls 52a and their toothed profiles 54a1 and 54a2 complementary.
La couronne d’aubages fixes 32a comporte un nombre déterminé de secteurs 34a de couronne dont la juxtaposition forme la totalité de la couronne d’aubages fixes 32a et elle comprend au moins deux de ces secteurs angulaires de couronne d’aubages 34a comportant des profils dentés complémentaires 54a1 , 54a2. Il sera compris que bien évidemment, tous les secteurs 34a de couronne comportent de préférence des profils dentés. Ainsi, chaque secteur angulaire 34a est assemblé avec chacun des secteurs angulaires 34a qui lui sont adjacents dans un assemblage du type décrit précédemment, et chaque bloc 44a comporte à ses deux extrémités des parois d'extrémités transversales opposées 52a qui sont conformées selon des profils dentés 54a1 , 54a2 destinés à coopérer avec les profils dentés 54a1 , 54a2 à dents d'orientation radiale des blocs 44a adjacents.  The fixed rotor crown 32a comprises a predetermined number of crown sectors 34a whose juxtaposition forms the entirety of the fixed crown 32a and comprises at least two of these angular crown sectors 34a having toothed profiles. 54a1, 54a2. It will be understood that, of course, all crown sectors 34a preferably comprise toothed profiles. Thus, each angular sector 34a is assembled with each of the angular sectors 34a which are adjacent to it in an assembly of the type described above, and each block 44a has at its two ends opposite transverse end walls 52a which are shaped according to toothed profiles. 54a1, 54a2 intended to cooperate with the toothed profiles 54a1, 54a2 with radially oriented teeth of the adjacent blocks 44a.
Dans le mode de réalisation préféré de l’invention, le bloc de matériau abradable 44a du secteur 34a s'étend jusqu'à la plateforme intérieure 40a. Cette configuration a été représentée à la figure 5B. Par rapport à un secteur angulaire 34a conventionnel comme celui qui a été représenté à la figure 5A, le pied 43a a été supprimé et le bloc 44a de matériau en nid d’abeilles a été étendu radialement jusqu’à la plateforme intérieure 40a de manière à conférer une hauteur maximale au bloc 44a de matériau en nid d’abeilles, et ce faisant, à lui conférer une étanchéité maximale. Par ailleurs, cette configuration permet de se dispenser de la mise en place d’un système d’étanchéité conventionnelle à languettes agencé sur le pied 43a.  In the preferred embodiment of the invention, the block of abradable material 44a of the sector 34a extends to the inner platform 40a. This configuration has been shown in Figure 5B. With respect to a conventional angular sector 34a as shown in FIG. 5A, the foot 43a has been removed and the block 44a of honeycomb material has been extended radially to the inner platform 40a so as to give a maximum height to the block 44a of honeycomb material, and in doing so, to give it maximum sealing. In addition, this configuration makes it possible to dispense with the installation of a conventional sealing system with tabs arranged on the foot 43a.
De préférence, comme l’illustre la figure 4, chaque plate-forme intérieure 40a comporte un bord d’extrémité 58a qui est conformé selon un profil denté 60a1 , 60a2 qui se superpose au profil denté 54a1 , 54a2 du bloc de matériau en nid abeilles 44a correspondant. Ainsi, les profils dentés 60a1 , 60a2 sont eux aussi complémentaires l’un de l’autre. Cette configuration n’est toutefois pas limitative de l’invention, et les bords d’extrémité 58a des plates-formes intérieures 40a pourraient être rectilignes. Preferably, as illustrated in Figure 4, each inner platform 40a has an end edge 58a which is shaped according to a toothed profile 60a1, 60a2 which is superimposed on the toothed profile 54a1, 54a2 of the block of honeycomb material 44a corresponding. Thus, toothed profiles 60a1, 60a2 are also complementary to one another. This However, the configuration is not limiting of the invention, and the end edges 58a of the inner platforms 40a could be rectilinear.
Chaque dent 56a1 ou 56a2 de chaque bloc 44a peut être réalisée de différentes façons. Par exemple, les dents 56a1 ou 56a2 pourraient être rapportées au bloc 44a, pourvu qu’elles fassent saillie à partir du bloc 44a. Toutefois, chaque dent 56a1 ou 56a2 est réalisée de préférence directement dans le matériau abradable en nid d'abeilles du bloc 44a.  Each tooth 56a1 or 56a2 of each block 44a can be made in different ways. For example, the teeth 56a1 or 56a2 could be reported to the block 44a, provided they protrude from the block 44a. However, each tooth 56a1 or 56a2 is preferably made directly in the abradable honeycomb material of the block 44a.
Le profil denté 54a1 , 54a2 du bloc de matériau en nid abeilles 44a peut prendre différentes configurations en fonction de l’étanchéité recherchée. Plus le nombre de dents 56a1 ou 56a2 est élevé, plus le profil 54a1 , 54a2 est à même de proposer un labyrinthe permettant de réduire efficacement le débit de flux de recirculation rc entre les secteurs angulaires adjacents 44a. En contrepartie, plus le nombre de dents 56a1 ou 56a2 est élevé, plus les tolérances d’ajustement de deux secteurs angulaires adjacents 44a sont réduites et plus ces secteurs adjacents 44a sont complexes à réaliser. Il sera donc compris que le nombre de dents 56a1 ou 56a2 résultera d’un compromis entre l’efficacité de la réduction du débit du flux de recirculation rc et le coût d’obtention de la couronne 32a formée des secteurs angulaires 34a, ce coût incluant la réalisation de ces secteurs 34a et leur assemblage.  The toothed profile 54a1, 54a2 of the block of honeycomb material 44a can take different configurations depending on the desired seal. The greater the number of teeth 56a1 or 56a2, the more the profile 54a1, 54a2 is able to provide a labyrinth to effectively reduce the recirculation flow rate rc between the adjacent angular sectors 44a. In return, the higher the number of teeth 56a1 or 56a2, the more the adjustment tolerances of two adjacent angular sectors 44a are reduced and these adjacent sectors 44a are more complex to achieve. It will therefore be understood that the number of teeth 56a1 or 56a2 will result from a compromise between the efficiency of reducing the flow rate of the recirculation flow rc and the cost of obtaining the ring 32a formed of the angular sectors 34a, this cost including the realization of these sectors 34a and their assembly.
Dans cette configuration, comme l’illustrent les figures 6 et 7, le profil denté 54a1 , 54a2 peut présenter, en section dans un plan perpendiculaire à une direction radiale R, une forme crénelée, c’est à dire comportant des dents de section sensiblement rectangulaire ou carrée.  In this configuration, as illustrated in FIGS. 6 and 7, the toothed profile 54a1, 54a2 may have, in section in a plane perpendicular to a radial direction R, a crenellated shape, ie having substantially sectioned teeth. rectangular or square.
En variante, comme l’illustre la figure 8, le profil denté 54a1 , 54a2 peut présenter, en section dans le plan perpendiculaire à la direction radiale R, une forme en dents de scie.  Alternatively, as shown in Figure 8, the toothed profile 54a1, 54a2 may have, in section in the plane perpendicular to the radial direction R, a sawtooth form.
En variante, comme l’illustre la figure 9, le profil denté 54a1 , 54a2 de chaque secteur 44a peut comporter un tenon qui constitue l’unique dent 56a1 , 56a2. En ce cas, l'unique dent 56a1 , 56a2 conformée en tenon s'étend à partir d'une des extrémités axiales 62a1 ou 62a2 du bloc 44a. Alternatively, as shown in Figure 9, the toothed profile 54a1, 54a2 of each sector 44a may comprise a tenon which is the only tooth 56a1, 56a2. In this case, the single tooth shaped tooth 56a1, 56a2 extends from one of the axial ends 62a1 or 62a2 of the block 44a.
Bien que cette configuration ne soit pas limitative de l’invention, il sera compris que le matériau abradable en nid d'abeilles du bloc 44a comporte des alvéoles tubulaires (non représentées) qui sont orientées radialement selon la direction radiale R. Cette configuration permet d’offrir le maximum de résistance au bloc de matériau 44a.  Although this configuration is not limiting of the invention, it will be understood that the abradable honeycomb material of the block 44a comprises tubular cells (not shown) which are oriented radially in the radial direction R. This configuration makes it possible to provide maximum resistance to the block of material 44a.
Dans le mode de réalisation préféré de l'invention, le matériau en nid d'abeilles du bloc 44a est obtenu par un procédé de fabrication additive. Cette configuration permet la formation d'alvéoles régulières et une conformation régulière des profils dentés 54a1 , 54a2 sans risque de détérioration comme pourrait risquer de le provoquer un procédé d'enlèvement de matière.  In the preferred embodiment of the invention, the honeycomb material of block 44a is obtained by an additive manufacturing process. This configuration allows the formation of regular cells and a regular conformation of toothed profiles 54a1, 54a2 without risk of deterioration as could risk causing a material removal process.
L’invention permet donc avantageusement d’assurer l’étanchéité entre des secteurs angulaires 32a de couronne d’aubages fixes de manière simple et efficace, et de limiter le débit du flux rc de recirculation entre ces secteurs angulaires 32a, ce qui permet d’améliorer de manière conséquente les performances d’un compresseur ou d’une turbine équipée de telle secteurs angulaires de couronne d’aubages 32a.  The invention therefore advantageously makes it possible to ensure the sealing between fixed rotor crown angular sectors 32a in a simple and effective manner, and to limit the flow rate of the recirculation flow rc between these angular sectors 32a, which makes it possible to significantly improve the performance of a compressor or a turbine equipped with such angular sectors of blade crown 32a.

Claims

REVENDICATIONS
1. Secteur angulaire (34a) de couronne d’aubages fixes (32a) de turbomachine (10), notamment de redresseur ou de distributeur, ledit secteur (34a) s'étendant suivant un angle déterminé autour d'un axe A de la couronne d’aubages fixes (32a) et comportant, par rapport à l'axe A de ladite couronne d’aubages fixes (32a), une plateforme radialement extérieure (38a), une plateforme radialement intérieure (40a), au moins deux aubes (42a) qui s'étendent entre lesdites plateformes (38a, 40a), et au moins un bloc de matériau abradable en nid d'abeilles (44a) qui s'étend intérieurement à la plateforme intérieure (38a) entre des extrémités transversales du secteur (34a), caractérisé en ce que le bloc (44a) de matériau abradable comporte au moins une paroi (52a) d'extrémité transversale qui est conformée selon un profil denté (54a1 , 54a2) comportant au moins une dent (56a1 , 56a2) d'orientation radiale (R), s'étendant suivant toute une épaisseur radiale dudit bloc (44a).  1. Angle sector (34a) fixed rotor crown (32a) turbomachine (10), including rectifier or distributor, said sector (34a) extending at a determined angle about an axis A of the crown of fixed blades (32a) and comprising, with respect to the axis A of said fixed crown ring (32a), a radially outer platform (38a), a radially inner platform (40a), at least two blades (42a). ) extending between said platforms (38a, 40a), and at least one block of abradable honeycomb material (44a) which extends internally to the inner platform (38a) between transverse ends of the sector (34a) ), characterized in that the block (44a) of abradable material comprises at least one wall (52a) of transverse end which is shaped according to a toothed profile (54a1, 54a2) comprising at least one tooth (56a1, 56a2) of radial orientation (R), extending along an entire radial thickness of said block (44a ).
2. Secteur angulaire (34a) selon la revendication précédente, caractérisé en ce que le bloc de matériau abradable (44a) s'étend jusqu'à la plateforme intérieure.  2. Angular sector (34a) according to the preceding claim, characterized in that the block of abradable material (44a) extends to the inner platform.
3. Secteur angulaire (34a) selon l'une des revendications précédentes, caractérisé en ce que chaque au moins une dent (56a1 , 56a2) fait saillie transversalement à partir dudit bloc (44a) et est réalisée dans ledit matériau abradable en nid d'abeilles dudit bloc (44a).  3. angular sector (34a) according to one of the preceding claims, characterized in that each at least one tooth (56a1, 56a2) protrudes transversely from said block (44a) and is made of said abradable nest material bees of said block (44a).
4. Secteur angulaire (34a) selon l'une des revendications précédentes, caractérisé en ce que le profil denté (54a1 , 54a2) présente, en section dans un plan perpendiculaire à la direction radiale (R), une forme en dents de scie.  4. Angle sector (34a) according to one of the preceding claims, characterized in that the toothed profile (54a1, 54a2) has, in section in a plane perpendicular to the radial direction (R), a sawtooth form.
5. Secteur angulaire (34a) selon l'une des revendications 1 à 3, caractérisé en ce que le profil denté (54a1 , 54a2) présente, en section dans un plan perpendiculaire à la direction radiale (R), une forme crenelée. 5. angular sector (34a) according to one of claims 1 to 3, characterized in that the toothed profile (54a1, 54a2) has, in section in a plane perpendicular to the radial direction (R), a crenelated form.
6. Secteur angulaire (34a) selon l'une des revendications 1 à 3, caractérisé en ce que le profil denté (54a1 , 54a2) comporte une unique dent (56a1 , 56a2) conformée en tenon. 6. Angle sector (34a) according to one of claims 1 to 3, characterized in that the toothed profile (54a1, 54a2) comprises a single tooth (56a1, 56a2) shaped tenon.
7. Secteur angulaire (34a) selon la revendication précédente, caractérisé en ce que l'unique dent (56a1 , 56a2) conformée en tenon s'étend à partir d'une des parois d’extrémité axiale du bloc.  7. Angle sector (34a) according to the preceding claim, characterized in that the single tooth (56a1, 56a2) shaped tenon extends from one of the axial end walls of the block.
8. Secteur angulaire (34a) selon l'une des revendications précédentes, caractérisé en ce que le matériau abradable en nid d'abeilles du bloc (44a) comporte des alvéoles tubulaires orientées radialement.  8. Angular sector (34a) according to one of the preceding claims, characterized in that the abradable honeycomb material of the block (44a) comprises radially oriented tubular cells.
9. Assemblage de deux secteurs angulaires adjacents (34a) selon l'une des revendications 1 à 8, caractérisé en ce que lesdites au moins une paroi d'extrémité transversale (52a) conformées selon des profils dentés (54a1 , 54a2) desdits secteurs angulaires adjacents (44a) sont tournées l'une vers l'autre, et en ce que lesdits profils dentés (54a1 , 54a2) sont complémentaires.  9. Assembly of two adjacent angular sectors (34a) according to one of claims 1 to 8, characterized in that said at least one transverse end wall (52a) shaped according to toothed profiles (54a1, 54a2) of said angular sectors. adjacent ones (44a) are rotated towards each other, and in that said toothed profiles (54a1, 54a2) are complementary.
10. Couronne d’aubages fixes (32a) de turbomachine comportant une pluralité de secteurs angulaires de couronne d'aubages fixes (34a), caractérisé en ce qu'elle comporte un nombre déterminé de secteurs (34a) dont la juxtaposition forme la totalité de la couronne d'aubages fixes (32a), en ce que chaque secteur angulaire (34a) comporte deux parois d'extrémités transversales opposées (52a) qui sont conformées selon des profils dentés (54a1 , 54a2) comportant chacun au moins une dent (56a1 , 56a2) d'orientation radiale, et en ce que chaque secteur angulaire (34a) est assemblé avec chacun des secteurs angulaires (34a) qui lui sont adjacents dans un assemblage selon la revendication 9.  10. A turbomachine fixed turbine crown (32a) comprising a plurality of fixed rotor crown angular sectors (34a), characterized in that it comprises a determined number of sectors (34a) whose juxtaposition forms the entire the ring of fixed blades (32a), in that each angular sector (34a) has two opposite transverse end walls (52a) which are shaped according to toothed profiles (54a1, 54a2) each comprising at least one tooth (56a1 , 56a2) of radial orientation, and in that each angular sector (34a) is assembled with each of the adjacent angular sectors (34a) in an assembly according to claim 9.
EP19740611.9A 2018-05-23 2019-05-22 Assembly of two adjacent angular sectors of turbomachine vane shroud and corresponding vane shroud Active EP3797213B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1854334A FR3081499B1 (en) 2018-05-23 2018-05-23 TURBOMACHINE BLADE ANGULAR SECTOR WITH IMPROVED WATERPROOFING
PCT/FR2019/051159 WO2019224476A1 (en) 2018-05-23 2019-05-22 Angular sector for turbomachine blading with improved sealing

Publications (2)

Publication Number Publication Date
EP3797213A1 true EP3797213A1 (en) 2021-03-31
EP3797213B1 EP3797213B1 (en) 2024-07-10

Family

ID=62816811

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19740611.9A Active EP3797213B1 (en) 2018-05-23 2019-05-22 Assembly of two adjacent angular sectors of turbomachine vane shroud and corresponding vane shroud

Country Status (6)

Country Link
US (1) US11686205B2 (en)
EP (1) EP3797213B1 (en)
CN (1) CN112292510B (en)
CA (1) CA3100958A1 (en)
FR (1) FR3081499B1 (en)
WO (1) WO2019224476A1 (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3119649B1 (en) * 2021-02-05 2023-04-21 Safran Aircraft Engines Inner support ring for the blades of a turbine engine compressor stator.
GB2606552B (en) * 2021-05-13 2023-11-22 Itp Next Generation Turbines S L Sealing system for gas turbine engine
FR3127517A1 (en) * 2021-09-27 2023-03-31 Safran Secondary stream cavity surface between a fixed wheel and a moving wheel of an improved turbomachine

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2452590A1 (en) * 1979-03-27 1980-10-24 Snecma REMOVABLE SEAL FOR TURBOMACHINE DISPENSER SEGMENT
FR2552159B1 (en) * 1983-09-21 1987-07-10 Snecma DEVICE FOR CONNECTING AND SEALING TURBINE STATOR BLADE SECTIONS
JP4494658B2 (en) * 2001-02-06 2010-06-30 三菱重工業株式会社 Gas turbine stationary blade shroud
JP2008180149A (en) * 2007-01-24 2008-08-07 Mitsubishi Heavy Ind Ltd Vane structure of gas turbine and gas turbine
US8910947B2 (en) * 2010-03-30 2014-12-16 United Technologies Corporation Method of forming a seal element
US9394800B2 (en) * 2013-01-21 2016-07-19 General Electric Company Turbomachine having swirl-inhibiting seal
DE102015204893B3 (en) * 2015-03-18 2016-06-09 MTU Aero Engines AG Protective device for a turbomachine
EP3375980B1 (en) * 2017-03-13 2019-12-11 MTU Aero Engines GmbH Seal holder for a flow engine
US10774670B2 (en) * 2017-06-07 2020-09-15 General Electric Company Filled abradable seal component and associated methods thereof

Also Published As

Publication number Publication date
FR3081499A1 (en) 2019-11-29
CN112292510A (en) 2021-01-29
FR3081499B1 (en) 2021-05-28
EP3797213B1 (en) 2024-07-10
US20210207488A1 (en) 2021-07-08
CA3100958A1 (en) 2019-11-28
WO2019224476A1 (en) 2019-11-28
US11686205B2 (en) 2023-06-27
CN112292510B (en) 2024-11-05

Similar Documents

Publication Publication Date Title
CA2834213C (en) Sealing device for a turbomachine turbine nozzle
EP3797213B1 (en) Assembly of two adjacent angular sectors of turbomachine vane shroud and corresponding vane shroud
EP3797212A1 (en) Turbomachine blading angular sector with seal between sectors
EP3049637B1 (en) Rotary assembly for turbomachine
FR2948726A1 (en) AUBES WHEEL COMPRISING IMPROVED COOLING MEANS
FR2966195A1 (en) SEALING ASSEMBLY FOR TURBOMACHINE
EP3794217A1 (en) Turbomachine stator element
CA2925438A1 (en) Rotary assembly for a turbomachine
FR2919345A1 (en) Cylindrical or truncated ring for e.g. jet prop engine, has internal slots housing internal blades between discharge ends of channels and internal longitudinal edges of radial surfaces, where blades extend on axial length of ring sectors
FR3013096A1 (en) SEALING SYSTEM WITH TWO ROWS OF COMPLEMENTARY LECHETTES
FR3068070B1 (en) TURBINE FOR TURBOMACHINE
FR2973829A1 (en) SEALING PLATE FOR AIRCRAFT TURBINE TURBINE TURBINE, COMPRISING ANTI-ROTATING FENSE TENONS
FR3091720A1 (en) SET FOR A TURBOMACHINE
WO2019069011A1 (en) Discharge duct of an intermediate housing hub for an aircraft turbojet engine comprising cooling channels
FR2999249A1 (en) High pressure axial compressor for e.g. turbojet for aircraft, has air draining unit for injecting cooling air between rotating element and static element such that cooling air immerses side of annular sealing ribs
EP3615774B1 (en) Device for sealing between a rotor and a stator of a turbine engine
FR3066533B1 (en) SEALING ASSEMBLY FOR A TURBOMACHINE
FR3092609A1 (en) TURBINE ASSEMBLY FOR AIRCRAFT TURBOMACHINE WITH IMPROVED DISC COOLING CIRCUIT
FR3009336A1 (en) ROTARY TURBOMACHINE ASSEMBLY WITH A VIROLE LABYRINTHE CMC
FR3079868A1 (en) LECHETTE OF SEAL BETWEEN ROTOR AND STATOR AND TURBINE SO EQUIPEE
FR3049000A1 (en) TURBINE DISPENSER COMPRISING A MONOBLOC INTERNAL CROWN
WO2014132001A1 (en) Reduction of convective exchanges between the air and the rotor in a turbine
WO2023156726A1 (en) Assembly for an aircraft turbomachine, and aircraft turbomachine
FR3127018A1 (en) Moving blade for a turbomachine turbine, having a design improving the sealing of the inter-blade cavities
EP4259906A1 (en) Turbine stator assembly with a radial degree of freedom between a guide vane assembly and a sealing ring

Legal Events

Date Code Title Description
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: UNKNOWN

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

Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE

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

Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE

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

Free format text: ORIGINAL CODE: 0009012

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

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20201218

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

DAV Request for validation of the european patent (deleted)
DAX Request for extension of the european patent (deleted)
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20220901

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20240202

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

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

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602019054980

Country of ref document: DE