EP2901021B2 - Turbomachine casing and impeller - Google Patents

Turbomachine casing and impeller Download PDF

Info

Publication number
EP2901021B2
EP2901021B2 EP13779269.3A EP13779269A EP2901021B2 EP 2901021 B2 EP2901021 B2 EP 2901021B2 EP 13779269 A EP13779269 A EP 13779269A EP 2901021 B2 EP2901021 B2 EP 2901021B2
Authority
EP
European Patent Office
Prior art keywords
groove
casing
strip
downstream
blades
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.)
Active
Application number
EP13779269.3A
Other languages
German (de)
French (fr)
Other versions
EP2901021A1 (en
EP2901021B1 (en
Inventor
Vincent Paul Gabriel Perrot
Sébastien COCHON
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
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=47505053&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP2901021(B2) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP2901021A1 publication Critical patent/EP2901021A1/en
Publication of EP2901021B1 publication Critical patent/EP2901021B1/en
Application granted granted Critical
Publication of EP2901021B2 publication Critical patent/EP2901021B2/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips

Definitions

  • the invention relates to an assembly comprising a turbomachine casing and a blade wheel disposed therein.
  • the casing can house one or more impellers, mounted for relative rotation inside the casing.
  • the blades are generally arranged in such a way that their ends pass as close as possible to the internal wall of the casing.
  • the internal surface of the casings of turbomachines is in certain cases equipped with a strip of abradable material (that is to say, intended to undergo abrasion), arranged inside the housing to the right of the end of the blades.
  • the length of the blades is then determined such that the blades, at full speed of the turbomachine, come into contact with the strip of abradable material.
  • the strip of abradable material wears until it reaches a shape which allows it to no longer come into contact with the blades.
  • the shape thus obtained is that which allows a minimum clearance between the end of the blades and the casing.
  • the international application WO2012/025357 presented a casing comprising a blade wheel, and in which the end of the blades is arranged so as to be substantially shorter on the downstream side than on the upstream side. This solution makes it possible to guarantee the existence of a clearance at least between the downstream part of the end of the blades and the casing.
  • turbomachines comprising moving blades inside fixed casings are moreover disclosed by the documents GB2361747 , EP1344895 , US 2012/163967 And JP 2009/174429 .
  • the object of the invention is therefore to propose an arrangement of casing and/or blades which makes it possible to minimize the play between the blades and the casing, which limits as much as possible the contacts and friction between the blades and the casing, and keeps the blades at maximum efficiency.
  • the casing/impeller assembly defined above which comprises, in line with the ends of the blades, a strip of abradable material on the upstream side, and a circumferential groove on the downstream side, has the following advantages.
  • the strip of abradable material is placed in line with the blade ends, on an upstream part thereof. However, it is at the level of the part upstream of the end of the blades that the reduction of the play between the end of the blades and the casing is the most useful.
  • the casing comprises a groove provided immediately downstream of the strip of abradable material.
  • the bottom of the groove is therefore recessed with respect to the strip of abradable material.
  • the groove has a larger radius than the strip of abradable material (more precisely, than the inner surface thereof).
  • This radius difference means that blades having a substantially constant radius from the leading edge to the trailing edge, may have ends having an upstream part very close to the strip of abradable material, so as to wear this strip when implementation of the turbomachine, in a manner known per se, and a downstream part not or very unlikely to come into contact with the surfaces of the groove and therefore the casing.
  • the downstream limit of the circumferential groove can be located to the right, or substantially to the right, of the downstream limit of the blade tips.
  • the downstream limit of the circumferential groove to be arranged axially downstream of the trailing edge of the blades.
  • the downstream limit of the circumferential groove is then preferably placed at an axial distance, relative to the trailing edge of the blades, of between 5 and 20% of the axial chord of the blade taken at the tip of the blade. This distance allows the circumferential groove to have a sufficient range of movement of the tip of the blade with respect to its nominal position.
  • the casing has an optimized contact surface, and advantageously comprises a strip of abradable material of minimum axial extent, which makes it possible to minimize the contacts and friction between the blades and the casing.
  • the invention further relates to a turbomachine axial flow compressor, comprising a casing or the assembly (casing and blade wheel) defined above.
  • the invention finally relates to a turbomachine comprising at least one casing as defined above.
  • FIG. 1 represents a turbomachine axial flow compressor 10.
  • This comprises a casing 12, inside which is mounted a blade wheel 14.
  • the blade wheel 14 itself comprises a rotor disc 16, on which are fixed manner known per se radial vanes 18, axisymmetrically.
  • the impeller is arranged so as to be able to rotate along an axis of rotation A inside the casing 12.
  • the casing 12 has an internal wall 20 delimiting a gas passage vein.
  • This internal wall forms a surface of revolution, which has a substantially conical general shape, and in the present case cylindrical, at the level (axially) of the blade wheel 14.
  • the upstream side of the casing 12 (with respect to the intended direction of circulation of the gases in the casing) is arranged on the left side of the figure.
  • Each of the vanes 18 has a leading edge 18A, a trailing edge 18B, and a tip 19.
  • the radially internal part of the casing 12 consists mainly of two parts: a substantially cylindrical sleeve 22 made of metal or metal alloy (alloy of titanium, aluminum, steel, etc.), and a strip 24 of abradable material, different from the material of part 22, for example an Al-Si based alloy.
  • the sleeve 22 Upstream and downstream of the blades 18, the sleeve 22 has a radially inner surface 23 that is substantially cylindrical.
  • the radius R of the latter is slightly greater than the maximum radius of the blade wheel 14, measured at the end of the blades 18.
  • the sleeve 22 does not include any internal channel or passage serving to ensure gas circulation at the right of the paddle wheel 14.
  • the sleeve 22 comprises a housing 26.
  • This has the shape of a circular circumferential groove, having a shape of revolution around the axis A, and formed hollow in the sleeve 22.
  • This housing 26 has a bottom surface 27 which is generally substantially cylindrical in shape.
  • the strip 24 which is also in the form of a sleeve, is placed in the housing 26 and occupies the upstream part thereof.
  • the housing has upstream, the strip 24 of abradable material, and downstream, a circumferential groove 30, which is simply the downstream part of the housing 26.
  • the band 24 has a radially inner surface 25.
  • the thickness (in the radial direction) of the sleeve 24 is determined in such a way that when the sleeve 24 is placed in the housing 26, the inner surfaces 23 of the sleeve 22 and 25 of the band 24 are continuous with each other, and have the same radius R ( figure 2 ).
  • the difference in radius between the surface 23 (inside the sleeve 22) and the bottom surface 27 of the housing 26, at the level of the strip 24, is thus equal to the thickness of the strip 24.
  • the upstream limit of the surface 25 of the strip 24 is arranged axially substantially in line with the leading edge 18A of the blades 18, or even slightly upstream of the latter.
  • the surface 25 of the strip 24 may have a discontinuity (of position and/or tangency) with respect to the surface 23.
  • the strip 24 could have a slightly smaller inside radius. , or slightly greater than the radius R of the surface 23 of the sleeve 22.
  • the downstream limit of the strip 24 is located approximately halfway (along the axis A) between the leading edge 18A and the trailing edge 18B of the blade 18.
  • the strip 24 of abradable material covers at least 30% of the axial extent of the blades. On the other hand, it is of little use for it to occupy more than 70% of the axial extent of the blades.
  • the groove 30 Immediately downstream of the strip 24 is the groove 30. This is delimited upstream by the strip 24, and at the bottom and on the downstream side by the sleeve 22.
  • the groove 30 generally comprises, from upstream to downstream, three successive parts: An upstream part 32 delimited by the strip 24, a bottom 34, and a downstream part 36.
  • the upstream part is formed by the downstream surface of the strip 24. Conversely, the bottom 34 and the downstream part 36 are not formed from an abradable material.
  • this surface is arranged in a plane transverse to the axis A of the housing 12.
  • the upstream surface 32 forms at the upstream end of the groove 30 an 'outgoing' staircase step, at the level of which the diameter fluid passage increases sharply.
  • the bottom surface 34 is a portion of the bottom surface of the housing 26.
  • the housing 26 has a cylindrical bottom surface and therefore in these embodiments, the bottom surfaces 27 are cylindrical.
  • downstream surface 36 of the groove 30 can be, like the surface 32, arranged in a plane transverse to the axis A of the housing 12 (embodiment of the picture 2 ).
  • the downstream surface 36 of the groove 30 forms at the downstream end of the groove 30 an 'inward' stair step, at the level of which the fluid passage diameter suddenly decreases to become equal to that of the surface. interior of room 22.
  • the downstream limit of the surface 36 of the groove 30 is arranged axially substantially in line with the trailing edge 18B of the blades 18, or even slightly downstream of the latter.
  • the groove 30 therefore has a concave axial section.
  • the axial extent of the bottom surface 34 is smaller than in the first embodiment, and conversely the axial extent of the downstream surface 36 is increased.
  • the surface 34 ends upstream of the trailing edge of the blades 18, and not to the right of this one.
  • the downstream surface 36 of the groove 30 therefore extends from the downstream limit of the bottom surface 34 upstream of the trailing edge of the blades 18, up to the level (axially) of this trailing edge or downstream of it. this.
  • downstream limit of the circumferential groove is arranged not in line with the trailing edge 18B of the blades, but downstream from the latter.
  • the downstream limit of the circumferential groove is thus arranged at an axial distance along the axis A, counted from the trailing edge 18B of the blades, comprised between 5 and 20% of the axial chord of the blades. taken at the top of dawn.
  • the value of the “axial chord of the blades” corresponds to the distance along the axis A, as shown in the figures, between the leading edge 18A and the trailing edge 18B of the blades.
  • the embodiment of the figure 5 is close to that of the figure 4 .
  • the only difference lies in the shape of the bottom of housing 26.
  • the bottom of the housing 26 is divided into two parts: an upstream part which receives the strip 24, and a downstream part which forms the groove 30. These two parts are both cylindrical in shape; the upstream part has a larger internal diameter than the downstream part, and consequently these two parts are separated by a shoulder 38.
  • This shoulder 38 serves to maintain the strip 34 in position, in particular in the axial direction.
  • This surface 40 has a strictly concave axial section (locally) at any point from upstream to downstream and consequently this surface section does not include a straight segment.
  • Its shape is any shape, which ideally is determined by use or by calculation so as to ensure that in all operating modes of the turbomachine, the surfaces 34 and 36 (and therefore the surface 40) remain without contact with the vanes 18.
  • figure 7 presents an embodiment which differs from that presented by the picture 3 by the shape of the upstream surface 32 of the groove 30.
  • the upstream surface 32 is frustoconical, with axis A. It forms with the latter an apex angle ⁇ of 45°.
  • the angle ⁇ is preferably at least equal to 45°.
  • the end 19 of the vanes 18 is located radially strictly inside the wall 20.
  • the length of the vanes is constant.
  • the blades may have a length (measured in the radial direction) which varies according to the position considered on the axis of the blade wheel.
  • the blades can thus have a total radius (overall radius of the blades mounted on the blade wheel) that is axially variable.
  • the blades can moreover have a total radius possibly greater or at least locally greater (that is to say only over a certain axial interval along the axis of the blade wheel) than the radius of the inner surface of the housing immediately upstream or downstream of the impeller.
  • the end of the blades then penetrates at least locally inside the wall of the casing.
  • the vanes can also present a non-uniform radial clearance with the casing, as shown by the embodiments presented above.
  • the overall radius of the vanes may be less or greater than the inside radius (R) of the housing surface immediately upstream or downstream of the vanes.
  • the total radius of the vanes can also vary between one and the other of these configurations depending on the position on the axis of the vane wheel.

Landscapes

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

Description

L'invention concerne un ensemble comportant un carter de turbomachine et une roue à aubes disposée dans celui-ci.The invention relates to an assembly comprising a turbomachine casing and a blade wheel disposed therein.

Le carter peut abriter une ou plusieurs roues à aubes, montée(s) à rotation relative à l'intérieur du carter.The casing can house one or more impellers, mounted for relative rotation inside the casing.

Pour optimiser le rendement de la turbomachine, en général les aubes sont agencées de telle manière que leurs extrémités passent aussi près que possible de la paroi interne du carter.To optimize the efficiency of the turbomachine, the blades are generally arranged in such a way that their ends pass as close as possible to the internal wall of the casing.

Cela entraîne que parfois, lors des premières heures de fonctionnement d'une turbomachine de moteur d'avion ou d'un turbomoteur d'hélicoptère, les extrémités des aubes rentrent en contact avec la paroi interne du carter, suite notamment à leur dilatation thermique et à leur allongement sous l'effet des forces centrifuges.This means that sometimes, during the first hours of operation of an airplane engine turbine engine or a helicopter turbine engine, the ends of the blades come into contact with the internal wall of the casing, following in particular their thermal expansion and to their elongation under the effect of centrifugal forces.

Pour éviter que ces contacts n'endommagent la paroi du carter, de manière connue en soi la surface interne de carters de turbomachines est dans certains cas équipée d'une bande de matériau abradable (c'est-à-dire, prévu pour subir une abrasion), agencée à l'intérieur du carter au droit de l'extrémité des aubes.To prevent these contacts from damaging the wall of the casing, in a manner known per se, the internal surface of the casings of turbomachines is in certain cases equipped with a strip of abradable material (that is to say, intended to undergo abrasion), arranged inside the housing to the right of the end of the blades.

La longueur des aubes est alors déterminée de telle sorte que les aubes, à plein régime de la turbomachine, entrent en contact avec la bande de matériau abradable.The length of the blades is then determined such that the blades, at full speed of the turbomachine, come into contact with the strip of abradable material.

Sous l'effet de ces frottements, lors des premières heures de fonctionnement de la turbomachine, la bande de matériau abradable s'use jusqu'à atteindre une forme qui permet qu'elle n'entre plus en contact avec les aubes. La forme ainsi obtenue est celle qui permet un jeu minimum entre l'extrémité des aubes et le carter.Under the effect of this friction, during the first hours of operation of the turbomachine, the strip of abradable material wears until it reaches a shape which allows it to no longer come into contact with the blades. The shape thus obtained is that which allows a minimum clearance between the end of the blades and the casing.

Cependant, les contacts et frottements qui se produisent entre la bande de matériau abradable et l'extrémité des aubes entraînent une usure, des vibrations voire des chocs préjudiciables à la pérennité et au bon fonctionnement de la turbomachine.However, the contacts and friction that occur between the strip of abradable material and the end of the blades lead to wear, vibrations and even shocks that are detrimental to the durability and correct operation of the turbomachine.

Il est donc nécessaire de minimiser l'importance de ceux-ci.It is therefore necessary to minimize the importance of these.

Dans ce but, la demande internationale WO2012/025357 a présenté un carter comprenant une roue à aubes, et dans lequel l'extrémité des aubes est aménagée de manière à être sensiblement plus courte sur le côté aval que sur le côté amont. Cette solution permet de garantir l'existence d'un jeu au moins entre la partie aval de l'extrémité des aubes et le carter.For this purpose, the international application WO2012/025357 presented a casing comprising a blade wheel, and in which the end of the blades is arranged so as to be substantially shorter on the downstream side than on the upstream side. This solution makes it possible to guarantee the existence of a clearance at least between the downstream part of the end of the blades and the casing.

Cependant, elle nécessite de réduire la surface des aubes et donc le travail apporté au fluide par celles-ci, diminuant ainsi le rendement de la roue à aubes.However, it requires reducing the surface area of the blades and therefore the work brought to the fluid by the latter, thus reducing the efficiency of the paddle wheel.

D'autres turbomachines comportant des aubes mobiles à l'intérieur de carters fixes sont par ailleurs divulguées par les documents GB2361747 , EP1344895 , US 2012/163967 et JP 2009/174429 .Other turbomachines comprising moving blades inside fixed casings are moreover disclosed by the documents GB2361747 , EP1344895 , US 2012/163967 And JP 2009/174429 .

L'objectif de l'invention est donc de proposer un agencement de carter et/ou d'aubes qui permette de minimiser le jeu entre les aubes et le carter, qui limite autant que possible les contacts et frottements entre les aubes et le carter, et conserve aux aubes une efficacité maximale.The object of the invention is therefore to propose an arrangement of casing and/or blades which makes it possible to minimize the play between the blades and the casing, which limits as much as possible the contacts and friction between the blades and the casing, and keeps the blades at maximum efficiency.

Cet objectif est atteint par un ensemble selon la revendication 1.This object is achieved by an assembly according to claim 1.

L'ensemble carter/roue à aubes défini ci-dessus, qui comporte, au droit des extrémités des aubes, une bande en matériau abradable du côté amont, et une rainure circonférentielle du côté aval, présente les avantages suivants.The casing/impeller assembly defined above, which comprises, in line with the ends of the blades, a strip of abradable material on the upstream side, and a circumferential groove on the downstream side, has the following advantages.

La bande de matériau abradable est placée au droit des extrémités d'aubes, sur une partie amont de celles-ci. Or, c'est au niveau de la partie amont de l'extrémité des aubes que la réduction du jeu entre l'extrémité des aubes et le carter est la plus utile.The strip of abradable material is placed in line with the blade ends, on an upstream part thereof. However, it is at the level of the part upstream of the end of the blades that the reduction of the play between the end of the blades and the casing is the most useful.

Par conséquent, c'est dans la partie amont de l'extrémité des aubes que l'utilisation d'une bande de matériau abradable est la plus justifiée. Elle permet, dans cette partie, d'obtenir un jeu minimum entre l'extrémité des aubes et le carter.Consequently, it is in the part upstream of the end of the blades that the use of a strip of abradable material is most justified. It allows, in this part, to obtain a minimum clearance between the end of the blades and the casing.

Inversement, dans la partie aval de l'extrémité des aubes, l'existence d'un jeu entre l'extrémité des aubes et le carter présente moins d'importance. Avantageusement selon l'invention, on privilégie donc dans cette partie la recherche d'une absence de collisions entre l'extrémité des aubes et le carter.Conversely, in the downstream part of the end of the blades, the existence of a clearance between the end of the blades and the casing is of less importance. Advantageously according to the invention, priority is therefore given in this part to the search for an absence of collisions between the end of the blades and the casing.

Dans ce but, selon l'invention le carter comporte une rainure aménagée immédiatement en aval de la bande de matériau abradable. Le fond de la rainure est donc en creux par rapport à la bande de matériau abradable. En d'autres termes, la rainure présente un rayon plus grand que la bande de matériau abradable (plus précisément, que la surface interne de celle-ci).For this purpose, according to the invention, the casing comprises a groove provided immediately downstream of the strip of abradable material. The bottom of the groove is therefore recessed with respect to the strip of abradable material. In other words, the groove has a larger radius than the strip of abradable material (more precisely, than the inner surface thereof).

Cet écart de rayon entraîne que des aubes présentant un rayon sensiblement constant du bord d'attaque au bord de fuite, pourront avoir des extrémités ayant une partie amont très proche de la bande de matériau abradable, de manière à user cette bande lors de la mise en œuvre de la turbomachine, de manière connue en soi, et une partie aval non ou très peu susceptible d'entrer en contact avec les surfaces de la rainure et donc le carter.This radius difference means that blades having a substantially constant radius from the leading edge to the trailing edge, may have ends having an upstream part very close to the strip of abradable material, so as to wear this strip when implementation of the turbomachine, in a manner known per se, and a downstream part not or very unlikely to come into contact with the surfaces of the groove and therefore the casing.

Pour une efficacité aérodynamique optimale de la roue à aubes, la limite aval de la rainure circonférentielle peut être située au droit, ou sensiblement au droit, de la limite aval des extrémités d'aubes.For optimal aerodynamic efficiency of the blade wheel, the downstream limit of the circumferential groove can be located to the right, or substantially to the right, of the downstream limit of the blade tips.

Selon une variante, pour éviter tout choc entre celles-ci et le carter, on peut aussi prévoir que la limite aval de la rainure circonférentielle soit disposée axialement en aval du bord de fuite des aubes.According to a variant, to avoid any shock between them and the casing, provision can also be made for the downstream limit of the circumferential groove to be arranged axially downstream of the trailing edge of the blades.

On dispose alors la limite aval de la rainure circonférentielle de préférence à une distance axiale, par rapport au bord de fuite des aubes, comprise entre 5 et 20% de la corde axiale de l'aube prise en sommet d'aube. Cette distance permet que la rainure circonférentielle présente une plage de débattement suffisante du sommet de l'aube par rapport à sa position nominale.The downstream limit of the circumferential groove is then preferably placed at an axial distance, relative to the trailing edge of the blades, of between 5 and 20% of the axial chord of the blade taken at the tip of the blade. This distance allows the circumferential groove to have a sufficient range of movement of the tip of the blade with respect to its nominal position.

Grâce à l'invention, le carter présente une surface de contact optimisée, et comporte avantageusement une bande de matériau abradable d'étendue axiale minimale, ce qui permet de minimiser les contacts et frottements entre les aubes et le carter.Thanks to the invention, the casing has an optimized contact surface, and advantageously comprises a strip of abradable material of minimum axial extent, which makes it possible to minimize the contacts and friction between the blades and the casing.

Les différents perfectionnements suivants peuvent avantageusement être prévus, seuls ou en combinaison :

  • la rainure, hormis une surface de rainure formée par la bande de matériau abradable, peut présenter une section axiale concave.
  • un fond de la rainure peut comprendre une portion cylindrique.
  • la rainure, hormis une surface de rainure formée par la bande de matériau abradable, peut présenter une section axiale concave en tout point de l'amont à l'aval.
  • la rainure peut être reliée du côté aval à la paroi interne du carter par un congé de raccordement concave, notamment ayant une section en arc de cercle.
  • la rainure peut être reliée du côté aval à la paroi interne du carter par une surface sensiblement tronconique.
  • le fond de la rainure peut présenter un rayon inférieur au rayon maximum de la bande de matériau abradable.
  • une surface de rainure peut être formée par la bande de matériau abradable et être de forme tronconique, l'angle du tronc de cône étant d'au moins 45°, et de préférence au moins 60°. Par extension, cette surface de la rainure formée par la bande de matériau abradable peut être formée dans un plan transverse au carter, et être perpendiculaire à l'axe du carter.
  • la rainure peut être étanche, ou présenter un fond étanche. En d'autres termes, la rainure n'est pas reliée à des conduits de circulation de gaz ou de fluide. Elle ne permet pas le prélèvement ou l'apport de gaz, mais sert uniquement à permettre la libre rotation des extrémités d'aubes en évitant les chocs entre celles-ci et le carter.
  • la bande de matériau abradable recouvre 30% à 70% de l'étendue axiale des aubes.
The various following improvements can advantageously be provided, alone or in combination:
  • the groove, apart from a groove surface formed by the strip of abradable material, may have a concave axial section.
  • a bottom of the groove may comprise a cylindrical portion.
  • the groove, apart from a groove surface formed by the strip of abradable material, may have a concave axial section at any point from upstream to downstream.
  • the groove can be connected on the downstream side to the internal wall of the casing by a concave fillet, in particular having an arcuate section.
  • the groove can be connected on the downstream side to the internal wall of the casing by a substantially frustoconical surface.
  • the bottom of the groove may have a radius less than the maximum radius of the strip of abradable material.
  • a groove surface may be formed by the strip of abradable material and be of frustoconical shape, the angle of the truncated cone being at least 45°, and preferably at least 60°. By extension, this surface of the groove formed by the strip of abradable material can be formed in a plane transverse to the casing, and be perpendicular to the axis of the casing.
  • the groove may be sealed, or have a sealed bottom. In other words, the groove is not connected to gas or fluid circulation conduits. It does not allow gas to be taken or supplied, but only serves to allow free rotation of the blade ends while avoiding shocks between them and the casing.
  • the strip of abradable material covers 30% to 70% of the axial extent of the blades.

L'invention vise en outre un compresseur à flux axial de turbomachine, comportant un carter ou l'ensemble (carter et roue à aubes) définis précédemment.The invention further relates to a turbomachine axial flow compressor, comprising a casing or the assembly (casing and blade wheel) defined above.

L'invention vise enfin une turbomachine comprenant au moins un carter tel que défini précédemment.The invention finally relates to a turbomachine comprising at least one casing as defined above.

L'invention sera bien comprise et ses avantages apparaîtront mieux à la lecture de la description détaillée qui suit, de modes de réalisation représentés à titre d'exemples non limitatifs. La description se réfère aux dessins annexés, sur lesquels :

  • la figure 1 est une vue schématique d'une portion de compresseur comprenant un carter selon l'invention ;
  • la figure 2 est une coupe schématique axiale d'une portion de compresseur, passant par une aube, dans un premier mode de réalisation de l'invention ;
  • la figure 3 est une coupe analogue à celle de la figure 2, présentant un deuxième mode de réalisation de l'invention ;
  • la figure 4 est une coupe analogue à celle de la figure 2, présentant un troisième mode de réalisation de l'invention ;
  • la figure 5 est une coupe analogue à celle de la figure 2, présentant un quatrième mode de réalisation de l'invention ;
  • la figure 6 est une coupe analogue à celle de la figure 2, présentant un exemple ne faisant pas partie de l'invention revendiquée; et
  • la figure 7 est une coupe analogue à celle de la figure 2, présentant un sixième mode de réalisation de l'invention.
The invention will be well understood and its advantages will appear better on reading the following detailed description of embodiments shown by way of non-limiting examples. The description refers to the accompanying drawings, in which:
  • there figure 1 is a schematic view of a compressor portion comprising a casing according to the invention;
  • there figure 2 is a diagrammatic axial section of a compressor portion, passing through a blade, in a first embodiment of the invention;
  • there picture 3 is a cut analogous to that of the figure 2 , presenting a second embodiment of the invention;
  • there figure 4 is a cut analogous to that of the figure 2 , presenting a third embodiment of the invention;
  • there figure 5 is a cut analogous to that of the figure 2 , presenting a fourth embodiment of the invention;
  • there figure 6 is a cut analogous to that of the figure 2 , showing an example not forming part of the claimed invention; And
  • there figure 7 is a cut analogous to that of the figure 2 , presenting a sixth embodiment of the invention.

La figure 1 représente un compresseur à flux axial de turbomachine 10. Celui-ci comprend un carter 12, à l'intérieur duquel est montée une roue à aubes 14. La roue à aubes 14 comprend elle-même un disque rotor 16, sur lequel sont fixées de manière connue en soi des aubes radiales 18, de manière axisymétrique. La roue à aubes est agencée de manière à pouvoir tourner suivant un axe de rotation A à l'intérieur du carter 12.There figure 1 represents a turbomachine axial flow compressor 10. This comprises a casing 12, inside which is mounted a blade wheel 14. The blade wheel 14 itself comprises a rotor disc 16, on which are fixed manner known per se radial vanes 18, axisymmetrically. The impeller is arranged so as to be able to rotate along an axis of rotation A inside the casing 12.

Le carter 12 présente une paroi interne 20 délimitant une veine de passage de gaz. Cette paroi interne forme une surface de révolution, qui a une forme générale sensiblement conique, et dans le cas présent cylindrique, au niveau (axialement) de la roue à aubes 14.The casing 12 has an internal wall 20 delimiting a gas passage vein. This internal wall forms a surface of revolution, which has a substantially conical general shape, and in the present case cylindrical, at the level (axially) of the blade wheel 14.

L'agencement des aubes 18 et de la paroi interne 20 du carter 12 selon l'invention, dans différents modes de réalisation, est présenté dans les figures 2 à 7.The arrangement of the blades 18 and of the internal wall 20 of the casing 12 according to the invention, in different embodiments, is presented in the figures 2 to 7 .

Dans les différentes figures, les éléments identiques ou similaires comportent la même référence numérique. En outre, les différents carters présentés respectivement par les figures 3 à 7 sont identiques à celui présenté par la figure 2, à l'exception des différences signalées dans le texte.In the various figures, identical or similar elements have the same reference numeral. In addition, the various casings presented respectively by the figures 3 to 7 are identical to that presented by the figure 2 , except for differences noted in the text.

Sur chacune des figures 2 à 7, le côté amont du carter 12 (par rapport au sens prévu de circulation des gaz dans le carter) est disposé sur le côté gauche de la figure.On each of figures 2 to 7 , the upstream side of the casing 12 (with respect to the intended direction of circulation of the gases in the casing) is arranged on the left side of the figure.

Chacune des aubes 18 présente un bord d'attaque 18A, un bord de fuite 18B, et une extrémité 19.Each of the vanes 18 has a leading edge 18A, a trailing edge 18B, and a tip 19.

Au niveau (axialement) de la roue à aubes 14, la partie radialement interne du carter 12 est constituée principalement de deux pièces : un manchon sensiblement cylindrique 22 en métal ou alliage métallique (alliage de titane, aluminium, acier, etc...), et une bande 24 en matériau abradable, différent du matériau de la pièce 22, par exemple un alliage à base Al-Si.At the level (axially) of the bladed wheel 14, the radially internal part of the casing 12 consists mainly of two parts: a substantially cylindrical sleeve 22 made of metal or metal alloy (alloy of titanium, aluminum, steel, etc.), and a strip 24 of abradable material, different from the material of part 22, for example an Al-Si based alloy.

En amont et en aval des aubes 18, le manchon 22 présente une surface radialement intérieure 23 sensiblement cylindrique. Le rayon R de celle-ci est légèrement supérieur au rayon maximal de la roue à aubes 14, mesuré à l'extrémité des aubes 18. Le manchon 22 ne comporte aucun canal ou passage interne servant à assurer une circulation de gaz au droit de la roue à aubes 14.Upstream and downstream of the blades 18, the sleeve 22 has a radially inner surface 23 that is substantially cylindrical. The radius R of the latter is slightly greater than the maximum radius of the blade wheel 14, measured at the end of the blades 18. The sleeve 22 does not include any internal channel or passage serving to ensure gas circulation at the right of the paddle wheel 14.

En regard ou au droit des extrémités des aubes 18, le manchon 22 comporte un logement 26. Celui-ci a la forme d'une rainure circonférentielle circulaire, ayant une forme de révolution autour de l'axe A, et formée en creux dans le manchon 22. Ce logement 26 présente une surface de fond 27 qui est de forme générale sensiblement cylindrique.Opposite or in line with the ends of the blades 18, the sleeve 22 comprises a housing 26. This has the shape of a circular circumferential groove, having a shape of revolution around the axis A, and formed hollow in the sleeve 22. This housing 26 has a bottom surface 27 which is generally substantially cylindrical in shape.

La bande 24, qui est également en forme de manchon, est disposée dans le logement 26 et occupe la partie amont de celui-ci.The strip 24, which is also in the form of a sleeve, is placed in the housing 26 and occupies the upstream part thereof.

Par suite, en regard des extrémités des aubes 18, le carter présente en amont, la bande 24 de matériau abradable, et en aval, une rainure circonférentielle 30, qui est simplement la partie aval du logement 26.As a result, facing the ends of the blades 18, the housing has upstream, the strip 24 of abradable material, and downstream, a circumferential groove 30, which is simply the downstream part of the housing 26.

La bande 24 présente une surface radialement intérieure 25. L'épaisseur (suivant la direction radiale) du manchon 24 est déterminée de telle manière que lorsque le manchon 24 est disposé dans le logement 26, les surfaces intérieures 23 du manchon 22 et 25 de la bande 24 soient dans la continuité l'une de l'autre, et présentent un même rayon R (figure 2). La différence de rayon entre la surface 23 (intérieur du manchon 22) et la surface de fond 27 du logement 26, au niveau de la bande 24, est ainsi égale à l'épaisseur de la bande 24.The band 24 has a radially inner surface 25. The thickness (in the radial direction) of the sleeve 24 is determined in such a way that when the sleeve 24 is placed in the housing 26, the inner surfaces 23 of the sleeve 22 and 25 of the band 24 are continuous with each other, and have the same radius R ( figure 2 ). The difference in radius between the surface 23 (inside the sleeve 22) and the bottom surface 27 of the housing 26, at the level of the strip 24, is thus equal to the thickness of the strip 24.

La limite amont de la surface 25 de la bande 24 est disposée axialement sensiblement au droit du bord d'attaque 18A des aubes 18, voire légèrement en amont de celui-ci.The upstream limit of the surface 25 of the strip 24 is arranged axially substantially in line with the leading edge 18A of the blades 18, or even slightly upstream of the latter.

Notons que dans le cadre de l'invention, la surface 25 de la bande 24 peut présenter une discontinuité (de position et/ou de tangence) par rapport à la surface 23. Par exemple, la bande 24 pourrait présenter un rayon intérieur légèrement inférieur, ou légèrement supérieur, au rayon R de la surface 23 du manchon 22.It should be noted that in the context of the invention, the surface 25 of the strip 24 may have a discontinuity (of position and/or tangency) with respect to the surface 23. For example, the strip 24 could have a slightly smaller inside radius. , or slightly greater than the radius R of the surface 23 of the sleeve 22.

La limite aval de la bande 24 est située environ à mi-distance (suivant l'axe A) entre le bord d'attaque 18A et le bord de fuite 18B de l'aube 18. De manière générale, il est préférable que la bande 24 en matériau abradable recouvre au moins 30% de l'étendue axiale des aubes. D'autre part, il est peu utile qu'elle occupe plus de 70% de l'étendue axiale des aubes.The downstream limit of the strip 24 is located approximately halfway (along the axis A) between the leading edge 18A and the trailing edge 18B of the blade 18. In general, it is preferable that the strip 24 of abradable material covers at least 30% of the axial extent of the blades. On the other hand, it is of little use for it to occupy more than 70% of the axial extent of the blades.

Immédiatement en aval de la bande 24 se trouve la rainure 30. Celle-ci est délimitée en amont par la bande 24, et au fond et du côté aval par le manchon 22.Immediately downstream of the strip 24 is the groove 30. This is delimited upstream by the strip 24, and at the bottom and on the downstream side by the sleeve 22.

La rainure 30 comporte généralement, de l'amont vers l'aval, trois parties successives : Une partie amont 32 délimitée par la bande 24, un fond 34, et une partie aval 36.The groove 30 generally comprises, from upstream to downstream, three successive parts: An upstream part 32 delimited by the strip 24, a bottom 34, and a downstream part 36.

La partie amont est formée par la surface aval de la bande 24. Inversement, le fond 34 et la partie aval 36 ne sont pas formés en matériau abradable.The upstream part is formed by the downstream surface of the strip 24. Conversely, the bottom 34 and the downstream part 36 are not formed from an abradable material.

Ils sont formés directement dans le manchon 22.They are formed directly in the sleeve 22.

Dans les modes de réalisation des figures 2 à 6, cette surface est disposée dans un plan transverse à l'axe A du carter 12. Par suite, la surface amont 32 forme à l'extrémité amont de la rainure 30 une marche d'escalier 'sortante', au niveau de laquelle le diamètre de passage du fluide augmente brutalement.In the embodiments of figures 2 to 6 , this surface is arranged in a plane transverse to the axis A of the housing 12. As a result, the upstream surface 32 forms at the upstream end of the groove 30 an 'outgoing' staircase step, at the level of which the diameter fluid passage increases sharply.

La surface de fond 34 est une partie de la surface de fond du logement 26. Dans les modes de réalisation des figures 2 à 4 et 7, le logement 26 présente une surface de fond cylindrique et par suite dans ces modes de réalisation, les surfaces de fond 27 sont cylindriques.The bottom surface 34 is a portion of the bottom surface of the housing 26. In embodiments of the figures 2 to 4 And 7 , the housing 26 has a cylindrical bottom surface and therefore in these embodiments, the bottom surfaces 27 are cylindrical.

Enfin, la surface aval 36 de la rainure 30 peut être, comme la surface 32, disposée dans un plan transverse à l'axe A du carter 12 (mode de réalisation de la figure 2). Par suite, la surface aval 36 de la rainure 30 forme à l'extrémité aval de la rainure 30 une marche d'escalier 'rentrante', au niveau de laquelle le diamètre de passage du fluide diminue brutalement pour redevenir égal à celui de la surface intérieure de la pièce 22.Finally, the downstream surface 36 of the groove 30 can be, like the surface 32, arranged in a plane transverse to the axis A of the housing 12 (embodiment of the picture 2 ). As a result, the downstream surface 36 of the groove 30 forms at the downstream end of the groove 30 an 'inward' stair step, at the level of which the fluid passage diameter suddenly decreases to become equal to that of the surface. interior of room 22.

La limite aval de la surface 36 de la rainure 30 est disposée axialement sensiblement au droit du bord de fuite 18B des aubes 18, voire légèrement en aval de celui-ci.The downstream limit of the surface 36 of the groove 30 is arranged axially substantially in line with the trailing edge 18B of the blades 18, or even slightly downstream of the latter.

La rainure 30 présente donc une section axiale concave.The groove 30 therefore has a concave axial section.

Les figures 3 à 7 présentent différents modes de réalisation de la rainure 30.THE figures 3 to 7 present different embodiments of the groove 30.

Les modes de réalisation des figures 3 et 4 diffèrent de celui de la figure 2 par l'agencement de la surface aval 36 de la rainure 30 :

  • Sur la figure 3, la surface aval 36 est de forme tronconique, d'axe A. Ainsi, la rainure 30 est reliée du côté aval à la paroi interne 20 du carter par une surface sensiblement tronconique, formant en section axiale une pente constante reliant le fond 34 à la paroi 20 du carter. Cette forme avantageusement limite la formation de turbulences au niveau de la partie aval de l'extrémité des aubes 18.
  • Sur la figure 4, la surface aval 36 est un congé de raccordement concave, ayant une section en arc de cercle. La limite amont de ce congé de raccordement est en continuité de position et de tangence avec le fond 34 de la rainure 30.
The embodiments of figures 3 and 4 differ from that of the picture 2 by the arrangement of the downstream surface 36 of the groove 30:
  • On the picture 3 , the downstream surface 36 is of frustoconical shape, with axis A. Thus, the groove 30 is connected on the downstream side to the internal wall 20 of the casing by a substantially frustoconical surface, forming in axial section a constant slope connecting the bottom 34 to the wall 20 of the housing. This shape advantageously limits the formation of turbulence at the level of the downstream part of the end of the blades 18.
  • On the figure 4 , the downstream surface 36 is a concave fillet, having an arcuate section. The upstream limit of this fillet is continuous in position and tangency with the bottom 34 of the groove 30.

En outre dans ces deux modes de réalisation, l'étendue axiale de la surface de fond 34 est plus faible que dans le premier mode de réalisation, et inversement l'étendue axiale de la surface aval 36 est accrue. En effet dans ces modes de réalisation, la surface 34 s'achève en amont du bord de fuite des aubes 18, et non au droit de celui-ci. La surface aval 36 de la rainure 30 s'étend donc depuis la limite aval de la surface de fond 34 en amont du bord de fuite des aubes 18, jusqu'au niveau (axialement) de ce bord de fuite ou en aval de celui-ci.Furthermore, in these two embodiments, the axial extent of the bottom surface 34 is smaller than in the first embodiment, and conversely the axial extent of the downstream surface 36 is increased. Indeed in these embodiments, the surface 34 ends upstream of the trailing edge of the blades 18, and not to the right of this one. The downstream surface 36 of the groove 30 therefore extends from the downstream limit of the bottom surface 34 upstream of the trailing edge of the blades 18, up to the level (axially) of this trailing edge or downstream of it. this.

D'autre part, dans les modes de réalisation des figures 3, 4 ainsi que dans l'example de la figure 6 qui n'est pas couvert par les revendications, la limite aval de la rainure circonférentielle est disposée non pas au droit du bord de fuite 18B des aubes, mais en aval de celui-ci.On the other hand, in the embodiments of figures 3, 4 as well as in the example of figure 6 which is not covered by the claims, the downstream limit of the circumferential groove is arranged not in line with the trailing edge 18B of the blades, but downstream from the latter.

Dans ces différents modes de réalisation, la limite aval de la rainure circonférentielle est ainsi disposée à une distance axiale suivant l'axe A, comptée à partir du bord de fuite 18B des aubes, comprise entre 5 et 20% de la corde axiale des aubes prise en sommet d'aube. La valeur de la 'corde axiale des aubes' correspond à la distance suivant l'axe A, telle que représentée sur les figures, entre le bord d'attaque 18A et le bord de fuite 18B des aubes.In these various embodiments, the downstream limit of the circumferential groove is thus arranged at an axial distance along the axis A, counted from the trailing edge 18B of the blades, comprised between 5 and 20% of the axial chord of the blades. taken at the top of dawn. The value of the “axial chord of the blades” corresponds to the distance along the axis A, as shown in the figures, between the leading edge 18A and the trailing edge 18B of the blades.

Le mode de réalisation de la figure 5 est voisin de celui de la figure 4. La seule différence tient à la forme du fond du logement 26.The embodiment of the figure 5 is close to that of the figure 4 . The only difference lies in the shape of the bottom of housing 26.

En effet, contrairement aux modes de réalisation des figures 2 à 4, dans le mode de réalisation de la figure 5, le fond du logement 26 est divisé en deux parties : une partie amont qui reçoit la bande 24, et une partie aval qui forme la rainure 30. Ces deux parties sont toutes deux de forme cylindrique ; la partie amont a un diamètre intérieur plus élevé que la partie aval, et par suite, ces deux parties sont séparées par un épaulement 38.Indeed, unlike the embodiments of figures 2 to 4 , in the embodiment of the figure 5 , the bottom of the housing 26 is divided into two parts: an upstream part which receives the strip 24, and a downstream part which forms the groove 30. These two parts are both cylindrical in shape; the upstream part has a larger internal diameter than the downstream part, and consequently these two parts are separated by a shoulder 38.

Cet épaulement 38 sert à assurer le maintien en position de la bande 34, notamment suivant la direction axiale.This shoulder 38 serves to maintain the strip 34 in position, in particular in the axial direction.

La figure 6 présente un exemple non revendiqué dans lequel les surfaces de fond 34 et aval 36 sont continues ; aucune limite entre celles-ci n'est perceptible.There figure 6 presents a non-claimed example in which the bottom 34 and downstream 36 surfaces are continuous; no limit between them is perceptible.

La réunion des surfaces 34 et 36 constitue une surface 40.The union of surfaces 34 and 36 constitutes a surface 40.

Cette surface 40 présente une section axiale strictement concave (localement) en tout point de l'amont à l'aval et par suite, cette section de surface ne comporte pas de segment de droite. Sa forme est une forme quelconque, qui idéalement est déterminée à l'usage ou par calcul de manière à assurer que dans tous les modes de fonctionnement de la turbomachine, les surfaces 34 et 36 (et donc la surface 40) restent sans contact avec les aubes 18.This surface 40 has a strictly concave axial section (locally) at any point from upstream to downstream and consequently this surface section does not include a straight segment. Its shape is any shape, which ideally is determined by use or by calculation so as to ensure that in all operating modes of the turbomachine, the surfaces 34 and 36 (and therefore the surface 40) remain without contact with the vanes 18.

Enfin, la figure 7 présente un mode de réalisation qui diffère de celui présenté par la figure 3 par la forme de la surface amont 32 de la rainure 30.Finally, the figure 7 presents an embodiment which differs from that presented by the picture 3 by the shape of the upstream surface 32 of the groove 30.

En effet, au lieu que cette surface amont soit perpendiculaire à l'axe A du carter, la surface amont 32 est tronconique, d'axe A. Elle forme avec ce dernier un angle au sommet α de 45°.Indeed, instead of this upstream surface being perpendicular to the axis A of the casing, the upstream surface 32 is frustoconical, with axis A. It forms with the latter an apex angle α of 45°.

Pour éviter de surdimensionner inutilement la bande de matériau abradable 24, l'angle α est de préférence au moins égal à 45°.To avoid unnecessarily oversizing the strip of abradable material 24, the angle α is preferably at least equal to 45°.

Dans les différents modes de réalisation présentés, l'extrémité 19 des aubes 18 est située radialement strictement à l'intérieur de la paroi 20. De plus, la longueur des aubes (mesurée suivant la direction radiale) est constante.In the different embodiments presented, the end 19 of the vanes 18 is located radially strictly inside the wall 20. In addition, the length of the vanes (measured in the radial direction) is constant.

Aucune de ces deux caractéristiques n'est indispensable à l'invention.Neither of these two characteristics is essential to the invention.

Dans le cadre de l'invention, les aubes peuvent avoir une longueur (mesurée suivant la direction radiale) qui varie en fonction de la position considérée sur l'axe de la roue à aubes. Les aubes peuvent ainsi présenter un rayon total (rayon hors tout des aubes montées sur la roue à aubes) axialement variable.In the context of the invention, the blades may have a length (measured in the radial direction) which varies according to the position considered on the axis of the blade wheel. The blades can thus have a total radius (overall radius of the blades mounted on the blade wheel) that is axially variable.

Dans le cadre de l'invention, les aubes peuvent par ailleurs présenter un rayon total éventuellement supérieur ou du moins localement supérieur (c'est-à-dire seulement sur un certain intervalle axial suivant l'axe de la roue à aubes) au rayon de la surface interne du carter immédiatement en amont ou en aval de la roue à aubes. L'extrémité des aubes pénètre alors au moins localement à l'intérieur de la paroi du carter.In the context of the invention, the blades can moreover have a total radius possibly greater or at least locally greater (that is to say only over a certain axial interval along the axis of the blade wheel) than the radius of the inner surface of the housing immediately upstream or downstream of the impeller. The end of the blades then penetrates at least locally inside the wall of the casing.

Les aubes peuvent d'autre part présenter un jeu radial non uniforme avec le carter, comme le montrent les modes de réalisation présentés précédemment.The vanes can also present a non-uniform radial clearance with the casing, as shown by the embodiments presented above.

Par conséquent, le rayon total des aubes peut être inférieur ou supérieur au rayon intérieur (R) de la surface de carter immédiatement en amont ou en aval des aubes. Le rayon total des aubes peut aussi varier entre l'une et l'autre de ces configurations en fonction de la position sur l'axe de la roue à aubes.Therefore, the overall radius of the vanes may be less or greater than the inside radius (R) of the housing surface immediately upstream or downstream of the vanes. The total radius of the vanes can also vary between one and the other of these configurations depending on the position on the axis of the vane wheel.

Claims (9)

  1. An assembly comprising a turbine engine casing (12) and a bladed rotor wheel (14), the blades being radial, arranged inside said casing, the bladed rotor wheel (14) having an axis of rotation (A) and comprising a rotor disk (16) having the blades fastened thereto in axisymmetric manner; the casing (12) presenting an inside wall (20) including a circumferential strip (24) of abradable material; wherein
    in register with the tips of the blades, the casing presents upstream, the strip of abradable material, so as to provide minimum clearance between the blade tips and the casing, and downstream a circumferential groove (30);
    the strip of abradable material being defined downstream by the circumferential groove (30);
    a downstream end of the circumferential groove (30) is arranged axially in register with or downstream from the trailing edges (18B) of the blades (18);
    the circumferential groove (30) presents from upstream to downstream, three successive portions, namely an upstream portion (32) defined by the strip (24), a bottom (34), and a downstream portion (36); and
    the bottom (34) of the circumferential groove (30) is cylindrical.
  2. An assembly according to claim 1, wherein the groove, apart from a groove surface (32) formed by the strip of abradable material, presents an axial section that is concave.
  3. An assembly according to claim 1 or 2, wherein the groove is connected on its downstream side to the inside wall (20) of the casing by a concave connection fillet (36), in particular having a circularly arcuate section.
  4. An assembly according to any one of claims 1 to 3, wherein the groove is connected on its downstream side to the inside wall of the casing by a surface (36) that is substantially frustoconical.
  5. An assembly according to any one of claims 1 to 4, wherein a bottom (34) of the groove presents a radius that is less than the maximum radius of the strip of abradable material.
  6. An assembly according to any one of claims 1 to 5, wherein a groove surface formed by the strip of abradable material is frustoconical, the angle (α) of the truncated cone being at least 45°, and preferably at least 60°.
  7. An assembly according to any one of claims 1 to 6, the groove (30) presents a leaktight bottom.
  8. An assembly according to any one of claims 1 to 7, wherein the strip of abradable material covers 30% to 70% of the axial extent of said blades.
  9. A turbine engine, including at least one assembly according to any one of claims 1 to 8.
EP13779269.3A 2012-09-25 2013-09-19 Turbomachine casing and impeller Active EP2901021B2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1258959A FR2995949B1 (en) 2012-09-25 2012-09-25 TURBOMACHINE HOUSING
PCT/FR2013/052172 WO2014049239A1 (en) 2012-09-25 2013-09-19 Turbomachine casing and impeller

Publications (3)

Publication Number Publication Date
EP2901021A1 EP2901021A1 (en) 2015-08-05
EP2901021B1 EP2901021B1 (en) 2020-05-20
EP2901021B2 true EP2901021B2 (en) 2023-07-19

Family

ID=47505053

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13779269.3A Active EP2901021B2 (en) 2012-09-25 2013-09-19 Turbomachine casing and impeller

Country Status (9)

Country Link
US (1) US9982554B2 (en)
EP (1) EP2901021B2 (en)
JP (1) JP6382821B2 (en)
CN (1) CN104704244B (en)
BR (1) BR112015006386B1 (en)
CA (1) CA2885650C (en)
FR (1) FR2995949B1 (en)
RU (1) RU2727943C2 (en)
WO (1) WO2014049239A1 (en)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9598981B2 (en) * 2013-11-22 2017-03-21 Siemens Energy, Inc. Industrial gas turbine exhaust system diffuser inlet lip
EP3530957B1 (en) * 2017-02-08 2021-05-12 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Compressor and turbocharger
US10648484B2 (en) * 2017-02-14 2020-05-12 Honeywell International Inc. Grooved shroud casing treatment for high pressure compressor in a turbine engine
US10876423B2 (en) 2018-12-28 2020-12-29 Honeywell International Inc. Compressor section of gas turbine engine including hybrid shroud with casing treatment and abradable section
FR3091548B1 (en) 2019-01-09 2022-12-09 Safran Aircraft Engines Abradable turbomachine element provided with visual wear indicators
US10914318B2 (en) * 2019-01-10 2021-02-09 General Electric Company Engine casing treatment for reducing circumferentially variable distortion
US11015465B2 (en) 2019-03-25 2021-05-25 Honeywell International Inc. Compressor section of gas turbine engine including shroud with serrated casing treatment
US11078805B2 (en) * 2019-04-15 2021-08-03 Raytheon Technologies Corporation Inclination of forward and aft groove walls of casing treatment for gas turbine engine
JP7234178B2 (en) * 2020-03-19 2023-03-07 株式会社東芝 Storage device
KR102519091B1 (en) * 2021-05-28 2023-04-05 두산에너빌리티 주식회사 Design method for flowpath of axial compressor of gas turbine

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6227794B1 (en) † 1999-12-16 2001-05-08 Pratt & Whitney Canada Corp. Fan case with flexible conical ring

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4534698A (en) * 1983-04-25 1985-08-13 General Electric Company Blade containment structure
GB2245312B (en) * 1984-06-19 1992-03-25 Rolls Royce Plc Axial flow compressor surge margin improvement
JPH0835402A (en) 1994-07-26 1996-02-06 Ishikawajima Harima Heavy Ind Co Ltd Turbine casing structure
US5474417A (en) * 1994-12-29 1995-12-12 United Technologies Corporation Cast casing treatment for compressor blades
US5607284A (en) * 1994-12-29 1997-03-04 United Technologies Corporation Baffled passage casing treatment for compressor blades
US6382905B1 (en) * 2000-04-28 2002-05-07 General Electric Company Fan casing liner support
AU2002226029A1 (en) * 2000-11-06 2002-05-15 Advanced Components And Materials, Inc. Compliant brush shroud assembly for gas turbine engine compressors
US6585479B2 (en) 2001-08-14 2003-07-01 United Technologies Corporation Casing treatment for compressors
FR2832180B1 (en) * 2001-11-14 2005-02-18 Snecma Moteurs ABRADABLE COATING FOR WALLS OF GAS TURBINES
GB0206136D0 (en) * 2002-03-15 2002-04-24 Rolls Royce Plc Improvements in or relating to cellular materials
US20080041842A1 (en) 2005-09-07 2008-02-21 United Technologies Corporation Connector for heater
GB0526011D0 (en) * 2005-12-22 2006-02-01 Rolls Royce Plc Fan or compressor casing
FR2899274B1 (en) * 2006-03-30 2012-08-17 Snecma DEVICE FOR FASTENING RING SECTIONS AROUND A TURBINE WHEEL OF A TURBOMACHINE
JP4942206B2 (en) 2008-01-24 2012-05-30 株式会社日立製作所 Rotating machine
US8177494B2 (en) * 2009-03-15 2012-05-15 United Technologies Corporation Buried casing treatment strip for a gas turbine engine
FR2947016B1 (en) * 2009-06-17 2013-07-12 Snecma CENTRIFUGAL COMPRESSOR.
GB2483059A (en) 2010-08-23 2012-02-29 Rolls Royce Plc An aerofoil blade with a set-back portion
US9115594B2 (en) * 2010-12-28 2015-08-25 Rolls-Royce Corporation Compressor casing treatment for gas turbine engine
GB201103682D0 (en) * 2011-03-04 2011-04-20 Rolls Royce Plc A turbomachine casing assembly

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6227794B1 (en) † 1999-12-16 2001-05-08 Pratt & Whitney Canada Corp. Fan case with flexible conical ring

Also Published As

Publication number Publication date
EP2901021A1 (en) 2015-08-05
EP2901021B1 (en) 2020-05-20
BR112015006386B1 (en) 2022-05-24
BR112015006386A2 (en) 2017-07-04
US20150226078A1 (en) 2015-08-13
FR2995949A1 (en) 2014-03-28
US9982554B2 (en) 2018-05-29
RU2727943C2 (en) 2020-07-27
CN104704244A (en) 2015-06-10
WO2014049239A1 (en) 2014-04-03
CN104704244B (en) 2018-03-02
JP2015531447A (en) 2015-11-02
RU2015115673A (en) 2016-11-20
JP6382821B2 (en) 2018-08-29
CA2885650C (en) 2020-09-15
CA2885650A1 (en) 2014-04-03
FR2995949B1 (en) 2018-05-25

Similar Documents

Publication Publication Date Title
EP2901021B2 (en) Turbomachine casing and impeller
CA2714439C (en) Blade with non-axisymmetric platform: recess and boss on the extrados
EP2673472B1 (en) Blade-platform assembly for subsonic flow
EP2260179B1 (en) Blade with non-axisymmetric platform
EP2257694B1 (en) Blade with 3d platform comprising an inter-blade bulb
CA2518355C (en) Retention of centring keys of the rings under the variable setting stator blades of a gas turbine engine
CA2647057C (en) Sectorized distributor for a turbine
CA2801221C (en) Compressor and turbomachine with optimized efficiency
EP2795068B1 (en) Turbomachine compressor guide vanes assembly
EP3749838B1 (en) Vane for an aircraft turbine engine
WO2015092281A1 (en) Compressor shroud comprising a sealing element provided with a structure for driving and deflecting discharge air
EP3201438B1 (en) Rotor blade of a turbomachine comprising a flange which abuts a blocking notch of a rotor disc
EP2427659B1 (en) Stator shroud of aircraft turbine engine with slots for relieving mechanical stress on blades
WO2012072903A1 (en) Wear-resistant part for the support of a blade of a turbojet engine fan
EP3149286A1 (en) Sealing plate with fuse function
EP4088008B1 (en) Blade for a bladed rotor disk of an aircraft turbomachine, corresponding bladed rotor disk, turbine and turbomachine
WO2023041868A1 (en) Moving blade for a turbine of a turbine engine, comprising a stilt equipped with projections for radially retaining the blade
FR2944554A1 (en) High pressure turbine for turbo machine of aircraft, has downstream radial wall carrying axial support unit supported on upstream radial wall for axially retaining external structure of distributor with respect to case
WO2017187093A1 (en) Air flow rectification assembly and turbomachine comprising an assembly of this type
FR2933150A1 (en) Rectifier stage for high pressure compressor of e.g. ducted-fan turbine engine, in aircraft, has stiffening element i.e. sheet metal panel, provided with circular holes and fixed on downstream part and annular edge of outer ferrule
WO2024194567A1 (en) Sealing assembly for a turbomachine
FR3045709A1 (en) AUBE DE SOUFFLANTE
WO2016034804A1 (en) Rotational assembly provided with a wedging device

Legal Events

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

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20150320

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

DAX Request for extension of the european patent (deleted)
RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SAFRAN AIRCRAFT ENGINES

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: 20181128

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: 20200228

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: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

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: 602013069275

Country of ref document: DE

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1272777

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200615

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20200520

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

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200821

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200520

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200520

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200921

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200820

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200920

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

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200520

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200520

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200820

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200520

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1272777

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200520

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

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200520

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200520

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

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200520

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200520

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200520

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200520

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200520

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200520

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200520

REG Reference to a national code

Ref country code: DE

Ref legal event code: R026

Ref document number: 602013069275

Country of ref document: DE

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

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200520

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200520

PLBI Opposition filed

Free format text: ORIGINAL CODE: 0009260

PLAX Notice of opposition and request to file observation + time limit sent

Free format text: ORIGINAL CODE: EPIDOSNOBS2

26 Opposition filed

Opponent name: RAYTHEON TECHNOLOGIES CORPORATION

Effective date: 20210222

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

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200520

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200520

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20200930

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

Ref country code: LU

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

Effective date: 20200919

PLBB Reply of patent proprietor to notice(s) of opposition received

Free format text: ORIGINAL CODE: EPIDOSNOBS3

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

Ref country code: CH

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

Effective date: 20200930

Ref country code: BE

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

Effective date: 20200930

Ref country code: IE

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

Effective date: 20200919

Ref country code: LI

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

Effective date: 20200930

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

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200520

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200520

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200520

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

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200520

APAH Appeal reference modified

Free format text: ORIGINAL CODE: EPIDOSCREFNO

APBM Appeal reference recorded

Free format text: ORIGINAL CODE: EPIDOSNREFNO

APBP Date of receipt of notice of appeal recorded

Free format text: ORIGINAL CODE: EPIDOSNNOA2O

APBU Appeal procedure closed

Free format text: ORIGINAL CODE: EPIDOSNNOA9O

PUAH Patent maintained in amended form

Free format text: ORIGINAL CODE: 0009272

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

Free format text: STATUS: PATENT MAINTAINED AS AMENDED

27A Patent maintained in amended form

Effective date: 20230719

AK Designated contracting states

Kind code of ref document: B2

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: DE

Ref legal event code: R102

Ref document number: 602013069275

Country of ref document: DE

REG Reference to a national code

Ref country code: SE

Ref legal event code: RPEO

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

Ref country code: DE

Payment date: 20240820

Year of fee payment: 12

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

Ref country code: GB

Payment date: 20240820

Year of fee payment: 12

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

Ref country code: FR

Payment date: 20240820

Year of fee payment: 12

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

Ref country code: SE

Payment date: 20240820

Year of fee payment: 12

Ref country code: IT

Payment date: 20240820

Year of fee payment: 12