EP3827160A1 - Turbine blade - Google Patents

Turbine blade

Info

Publication number
EP3827160A1
EP3827160A1 EP19791311.4A EP19791311A EP3827160A1 EP 3827160 A1 EP3827160 A1 EP 3827160A1 EP 19791311 A EP19791311 A EP 19791311A EP 3827160 A1 EP3827160 A1 EP 3827160A1
Authority
EP
European Patent Office
Prior art keywords
blade
partition
platform
wiper
radially
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.)
Pending
Application number
EP19791311.4A
Other languages
German (de)
French (fr)
Inventor
Renaud James MARTET
Thomas Langevin
Cyril VERBRUGGE
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 EP3827160A1 publication Critical patent/EP3827160A1/en
Pending legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/712—Shape curved concave

Definitions

  • the present invention relates to a turbine blade for a turbomachine, such as for example an aircraft turbojet.
  • Document FR 2 970 999 in the name of the Applicant discloses a bladed turbine wheel comprising a turbine disk on which blades 1 are mounted.
  • Each blade 1 extends radially and comprises a foot 2 radially internal, mounted in a disc cavity, a profiled blade 3, separated from the foot 2 by a radially internal platform 4.
  • a radially external platform 5 extends from the radially external end of the blade 3.
  • the radially external platform 5 comprises wipers 6 extending radially outwards which cooperate with an abradable material so as to form a labyrinth seal.
  • the external platform 5 has an axially upstream end 7 and an axially downstream end 8 located respectively upstream and downstream of the leading edge 9 and the trailing edge 10 of the blade 3.
  • the invention particularly aims to provide a simple, effective and economical solution to this problem.
  • the invention relates to a turbine blade for a turbomachine intended to extend around an axis of the turbomachine, the blade comprising a blade extending radially with respect to the axis between a radially internal platform and a radially external platform, the blade comprising an axially upstream leading edge and an axially downstream trailing edge, a radially external platform comprising an upstream end and a downstream end, the radially external platform comprising at minus a wiper extending radially outwards, characterized in that the radially external end of the leading edge of the blade and / or of the trailing edge of the blade extending axially upstream relative to the upstream end of the platform and / or respectively downstream relative to the downstream end of the platform, and in that the blade has at least one partition extending radially outwards from the end radially external to the blade, and axially between the leading edge and the upstream end
  • a partition extending radially outward and extending axially, that is to say along the axis of the turbine, between the leading edge of the 'blade and the upstream end of the platform and / or respectively between the trailing edge and the downstream end of the platform, constitutes at least in part an obstacle to air recirculation. Since these recirculations generate aerodynamic losses, such partitions also make it possible to improve the efficiency of the turbine.
  • the partition may extend axially between the leading edge and an upstream surface of the wiper and / or respectively between the trailing edge and a downstream surface of the wiper.
  • Such a partition makes it possible to prevent any recirculation of air radially outside the external platform.
  • the partition can extend radially outward substantially up to the radially outer end of the wiper.
  • the partition makes it possible to avoid recirculation of air all along the wiper which ensures, in cooperation with the abradable material, the seal at an air passage.
  • the partition may extend radially outwards over only part of the radial dimension of the wiper.
  • the radial distance between the radially outer end of the partition and the radially outer end of the wiper is for example between 1 and 10 mm.
  • the partition can extend in a direction forming an angle with the radial direction.
  • Such an inclination of the partition makes it possible to improve the position of the partition so that it opposes the direction of air recirculation from the lower surface to the upper surface.
  • the angle is for example between 30 ° and 60 °.
  • the partition may include an upstream and / or respectively downstream end edge, rectilinear and forming an angle with the radial direction.
  • the angle is for example between 0 ° and 60 °.
  • the wiper can extend along a plane, at least part of the partition extending perpendicular to the plane of the wiper.
  • the partition extends partly perpendicular to the wiper.
  • the wiper can extend along a plane, at least part of the partition extending along a plane forming an angle with the axis of the turbomachine.
  • the axis of the turbomachine corresponds to the axis of the rotor on which the blades are fixed.
  • the partition is thus inclined in the direction of the direction of rotation of the blade, so as to form a deflector for the air flow. Such a position thus effectively limits the recirculation of air from the lower surface to the upper surface.
  • Said angle is for example between 30 ° and 60 °.
  • the partition can be curved, for example concave viewed from the lower surface of the blade.
  • the invention also relates to a turbomachine turbine comprising a bladed wheel comprising turbine blades as described above.
  • the invention also relates to a turbomachine, such as for example an aircraft turbojet, characterized in that it comprises such a turbine.
  • FIG. 1 is a schematic view of a turbine blade of the prior art
  • FIG. 2 is a schematic view of an example of a turbine blade platform according to an embodiment of the invention.
  • FIGS. 3A to 4B are perspective views illustrating part of a blade according to different embodiments of the invention. DETAILED DESCRIPTION
  • upstream and downstream are defined with respect to the direction of flow of the gases in the turbomachine, in particular in the secondary stream.
  • radial and axial are defined relative to the axis of the turbine wheel. Each turbine blade extends radially outward from the disc of the turbine wheel, the axis of rotation of which extends axially.
  • Figure 2 illustrates part of a turbine blade 13 for a turbomachine according to the invention.
  • Several turbine blades 13 according to the invention are intended to be mounted on a disc so as to form a turbine wheel.
  • the blade 13 comprises a blade 14 extending radially, and a radially external platform 15 situated at the level of the radially external end of the blade 14.
  • the blade 14 comprises a leading edge 16 axially upstream and an axially downstream trailing edge (not shown).
  • the platform 15 includes an upstream end 17 and a downstream end (not shown). Said platform 15 also includes wipers, namely an upstream wiper 18 and a downstream wiper 19 in the example illustrated in the figures.
  • the platform 15 extends axially between the two wipers 18, 19 and is perforated with respect to the platform 5 of the prior art presented previously. Indeed, the platform 15 does not include a part extending axially beyond the wipers 18,19.
  • the radially outer end 20 of the leading edge 16 of the blade 14 extends axially upstream relative to the upstream end 17 of the platform 15.
  • the radially outer end of the trailing edge (not shown) of the blade 14 extends axially downstream relative to the downstream end of the platform 15.
  • the blade 13 according to the invention further comprises a partition 21.
  • the partition 21 is arranged radially outside the radially outer end 20 of the leading edge 16 and / or the trailing edge (not shown) of the blade. Indeed, the partition 21 extends circumferentially opposite the radially external end 20 of the blade 14.
  • the partition 21 extends axially between the leading edge 16 and the upstream end 17 of the platform15, and / or respectively between the trailing edge and the downstream end of the platform- shape 15.
  • the partition 21 illustrated extends axially between the leading edge 16 and an upstream surface 22 of the wiper 18. Similarly, it is conceivable that the partition 21 extends axially between the trailing edge and a surface downstream of the wiper.
  • the partition 21 extends over only part of the height, that is to say the radial dimension, of the wiper 18, 19 concerned.
  • the partition 21 has an end edge 23 rectilinear and forming an angle a with the radial direction or the radial plane.
  • the angle a is for example between 30 ° and 90 °.
  • the angle a is inscribed in a plane having for normal the axial direction.
  • the geometric shape and the positioning of the partitions 21 may vary depending on the applications.
  • the partition 21, 27 extends radially outwards substantially up to the radially external end 24, 26 of the wiper 18, 19.
  • the partition 21, 27 has a height substantially equivalent to that of the wiper 18, 19.
  • the partition 21, 27 extends radially outwards over only part of the radial dimension of the wiper 18, 19.
  • the radial distance between the radially outer end 25 of the partition 21, 27 and the radially outer end 24, 26 of the wiper 18, 19 is for example between 0.5 mm and 2 mm.
  • the partition 21 located at the level of the upstream wiper 18 and the partition 27 located at the level of the downstream wiper 19 can extend in a direction forming an angle b with the radial direction.
  • the angle b is for example between 0 ° and 60 °.
  • the angle b is inscribed in a plane comprising the axial and radial directions.
  • the downstream partition 27 extends, at least in part, along a plane forming an angle Q with the axis X of the turbomachine.
  • the partition and the wiper each extend radially projecting from the blade platform.
  • the partition 27 downstream is inclined in the direction of the direction of rotation of the blade R, so as to form a deflector for the air flow.
  • the downstream partition 27 is inclined towards the lower surface.
  • the inclination towards the lower surface is particularly interesting because it makes it more difficult to recirculate air from the lower surface to the upper surface.
  • Said angle Q is for example between 0 ° and 60 °.
  • the partition 21, 27 constitutes an obstacle to recirculation of air from the lower surface area to the upper surface area, and thus makes it possible to reduce the losses associated with such a recirculation. This increases the performance of the turbine, while limiting the mass of the blade 14 due to the limited dimensions of the external platform 15.

Landscapes

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

Abstract

The invention relates to a turbine blade (13) for a turbomachine, comprising a turbine blade airfoil (14) extending radially, said turbine blade airfoil (14) having a leading edge (16) axially upstream and a trailing edge axially downstream, a radially outer platform (15) having an upstream end (17) and a downstream end, said radially outer platform (15) further comprising at least one lip (18, 19) extending radially towards the outside, the radially outer end (20) of the leading edge (16) of the turbine blade airfoil (14) and/or of the trailing edge of the turbine blade airfoil (14) extending axially upstream in relation to the upstream end (17) of the platform (15) and/or, respectively, extending downstream in relation to the downstream end of the platform (15), characterized in that the blade (13) has at least one partition (21) extending radially towards the outside from the radially outer end of the turbine blade airfoil (14) and axially between the leading edge (16) and the upstream end (17) of the platform (15) and/or, respectively, between the trailing edge and the downstream end of the platform (15).

Description

AUBE DE TURBINE  TURBINE DAWN
DOMAINE FIELD
[001] La présente invention concerne une aube de turbine pour une turbomachine, telle par exemple qu’un turboréacteur d’avion. CONTEXTE The present invention relates to a turbine blade for a turbomachine, such as for example an aircraft turbojet. CONTEXT
[002] Le document FR 2 970 999 au nom de la Demanderesse divulgue une roue aubagée de turbine comportant un disque de turbine sur lequel sont montées des aubes 1. Chaque aube 1 s’étend radialement et comporte un pied 2 radialement interne, monté dans un alvéole du disque, une pale 3 profilée, séparée du pied 2 par une plate-forme radialement interne 4. Une plate-forme radialement externe 5 s’étend depuis l’extrémité radialement externe de la pale 3. La plate-forme radialement externe 5 comporte des léchettes 6 s’étendent radialement vers l’extérieur qui coopèrent avec un matériau abradable de manière à former un joint à labyrinthe. Document FR 2 970 999 in the name of the Applicant discloses a bladed turbine wheel comprising a turbine disk on which blades 1 are mounted. Each blade 1 extends radially and comprises a foot 2 radially internal, mounted in a disc cavity, a profiled blade 3, separated from the foot 2 by a radially internal platform 4. A radially external platform 5 extends from the radially external end of the blade 3. The radially external platform 5 comprises wipers 6 extending radially outwards which cooperate with an abradable material so as to form a labyrinth seal.
[003] La plate-forme externe 5 comporte une extrémité axialement amont 7 et une extrémité axialement aval 8 situées respectivement en amont et en aval du bord d’attaque 9 et du bord de fuite 10 de la pale 3. The external platform 5 has an axially upstream end 7 and an axially downstream end 8 located respectively upstream and downstream of the leading edge 9 and the trailing edge 10 of the blade 3.
[004] Afin d’alléger les aubes 1 , il est envisagé de retirer une partie de la plate-forme radialement externe 5 en formant des ajours au niveau de ladite plate-forme externe 5. Cependant, dans un tel cas, une partie du flux d’air peut être déviée de la zone d’intrados 11 vers la zone d’extrados 12 en passant radialement à l’extérieur de la pale 3, au travers des ajours. Une telle recirculation est néfaste pour le rendement de la turbine et il convient donc de la limiter. RESUME DE L’INVENTION  In order to lighten the blades 1, it is envisaged to remove a part of the radially external platform 5 by forming openings at the level of said external platform 5. However, in such a case, part of the air flow can be diverted from the lower surface 11 to the upper surface 12 by passing radially outside the blade 3, through the openings. Such recirculation is harmful to the efficiency of the turbine and should therefore be limited. SUMMARY OF THE INVENTION
[005] L’invention a notamment pour but d’apporter une solution simple, efficace et économique à ce problème. [006] A cet effet, l’invention concerne une aube de turbine pour une turbomachine destinée à s’étendre autour d’un axe de la turbomachine, l’aube comportant une pale s’étendant radialement par rapport à l’axe entre une plateforme radialement interne et une plateforme radialement externe, la pale comprenant un bord d’attaque axialement amont et un bord de fuite axialement aval, une plate-forme radialement externe comprenant une extrémité amont et une extrémité aval, la plate-forme radialement externe comprenant au moins une léchette s’étendant radialement vers l’extérieur, caractérisée en ce que l’extrémité radialement externe du bord d’attaque de la pale et/ou du bord de fuite de la pale s’étendant axialement vers l’amont par rapport à l’extrémité amont de la plate-forme et/ou respectivement vers l’aval par rapport à l’extrémité aval de la plate-forme, et en ce que l’aube comporte au moins une cloison s’étendant radialement vers l’extérieur depuis l’extrémité radialement externe de la pale, et axialement entre le bord d’attaque et l’extrémité amont de la plate-forme, et/ou respectivement entre le bord de fuite et l’extrémité aval de la plate-forme. The invention particularly aims to provide a simple, effective and economical solution to this problem. To this end, the invention relates to a turbine blade for a turbomachine intended to extend around an axis of the turbomachine, the blade comprising a blade extending radially with respect to the axis between a radially internal platform and a radially external platform, the blade comprising an axially upstream leading edge and an axially downstream trailing edge, a radially external platform comprising an upstream end and a downstream end, the radially external platform comprising at minus a wiper extending radially outwards, characterized in that the radially external end of the leading edge of the blade and / or of the trailing edge of the blade extending axially upstream relative to the upstream end of the platform and / or respectively downstream relative to the downstream end of the platform, and in that the blade has at least one partition extending radially outwards from the end radially external to the blade, and axially between the leading edge and the upstream end of the platform, and / or respectively between the trailing edge and the downstream end of the platform.
[007] Le retrait des extrémité amont et/ou aval par rapport au bord d’attaque et/ou par rapport au bord de fuite permet de limiter la dimension axiale de la plate-forme externe, et donc la masse de l’aube.  The withdrawal of the upstream and / or downstream end relative to the leading edge and / or relative to the trailing edge makes it possible to limit the axial dimension of the external platform, and therefore the mass of the blade.
[008] Par ailleurs, la présence d’une cloison, s’étendant radialement vers l’extérieur et s’étendant axialement, c’est-à-dire selon l’axe de la turbine, entre le bord d’attaque de l’aube et l’extrémité amont de la plate-forme et/ou respectivement entre le bord de fuite et l’extrémité aval de la plate-forme, constitue au moins en partie un obstacle à une recirculation d’air. Ces recirculations étant génératrices de pertes aérodynamiques, de telles cloisons permettent également d’améliorer le rendement de la turbine. Furthermore, the presence of a partition, extending radially outward and extending axially, that is to say along the axis of the turbine, between the leading edge of the 'blade and the upstream end of the platform and / or respectively between the trailing edge and the downstream end of the platform, constitutes at least in part an obstacle to air recirculation. Since these recirculations generate aerodynamic losses, such partitions also make it possible to improve the efficiency of the turbine.
[009] La cloison peut s’étendre axialement entre le bord d’attaque et une surface amont de la léchette et/ou respectivement entre le bord de fuite et une surface aval de la léchette.  The partition may extend axially between the leading edge and an upstream surface of the wiper and / or respectively between the trailing edge and a downstream surface of the wiper.
[010] Une telle cloison permet d’empêcher toute recirculation d’air radialement à l’extérieur de la plate-forme externe. [011] Selon une autre caractéristique, la cloison peut s’étendre radialement vers l’extérieur sensiblement jusqu’à l’extrémité radialement externe de la léchette. [010] Such a partition makes it possible to prevent any recirculation of air radially outside the external platform. According to another characteristic, the partition can extend radially outward substantially up to the radially outer end of the wiper.
[012] Ainsi, la cloison permet d’éviter la recirculation d’air tout le long de la léchette qui assure, en coopération avec le matériau abradable, l’étanchéité à un passage d’air.  [012] Thus, the partition makes it possible to avoid recirculation of air all along the wiper which ensures, in cooperation with the abradable material, the seal at an air passage.
[013] Par ailleurs, la cloison peut s’étendre radialement vers l’extérieur sur une partie seulement de la dimension radiale de la léchette.  [013] Furthermore, the partition may extend radially outwards over only part of the radial dimension of the wiper.
[014] Ainsi, la présence de la cloison s’opposant à la recirculation d’air, la limitation de sa dimension radiale à une partie seulement de la dimension radiale de la léchette permet de contrôler l’ajout de matière, et donc de contrôler la masse de l’aube.  Thus, the presence of the partition opposing the recirculation of air, the limitation of its radial dimension to only part of the radial dimension of the wiper makes it possible to control the addition of material, and therefore to control the mass of dawn.
[015] La distance radiale entre l’extrémité radialement externe de la cloison et l’extrémité radialement externe de la léchette est par exemple comprise entre 1 et 10 mm.  The radial distance between the radially outer end of the partition and the radially outer end of the wiper is for example between 1 and 10 mm.
[016] La cloison peut s’étendre selon une direction formant un angle avec la direction radiale.  The partition can extend in a direction forming an angle with the radial direction.
[017] Une telle inclinaison de la cloison permet d’améliorer la position de la cloison de sorte qu’elle s’oppose au sens de recirculation d’air de l’intrados vers l’extrados.  Such an inclination of the partition makes it possible to improve the position of the partition so that it opposes the direction of air recirculation from the lower surface to the upper surface.
[018] L’angle est par exemple compris entre 30° et 60°.  The angle is for example between 30 ° and 60 °.
[019] Selon une autre caractéristique, la cloison peut comporter un bord d’extrémité amont et/ou respectivement aval, rectiligne et formant un angle avec la direction radiale.  According to another characteristic, the partition may include an upstream and / or respectively downstream end edge, rectilinear and forming an angle with the radial direction.
[020] Une telle inclinaison permet de réduire le volume de la cloison, et donc de contrôler la masse de la matière ajoutée à l’aube de la turbine. [020] Such an inclination makes it possible to reduce the volume of the partition, and therefore to control the mass of the material added to the blade of the turbine.
[021] L’angle est par exemple compris entre 0° et 60°.  The angle is for example between 0 ° and 60 °.
[022] De plus, la léchette peut s’étendre selon un plan, au moins une partie de la cloison s’étendant perpendiculairement au plan de la léchette.  [022] In addition, the wiper can extend along a plane, at least part of the partition extending perpendicular to the plane of the wiper.
[023] Par conséquent, la cloison s’étend en partie perpendiculairement à la léchette. [024] En particulier, la léchette peut s’étendre selon un plan, au moins une partie de la cloison s’étendant selon un plan formant un angle avec l’axe de la turbomachine. [023] Consequently, the partition extends partly perpendicular to the wiper. In particular, the wiper can extend along a plane, at least part of the partition extending along a plane forming an angle with the axis of the turbomachine.
[025] L’ axe de la turbomachine correspond à l’axe du rotor sur lequel sont fixées les aubes.  The axis of the turbomachine corresponds to the axis of the rotor on which the blades are fixed.
[026] La cloison est ainsi inclinée dans la direction du sens de rotation de l’aube, de manière à former un déflecteur pour le flux d’air. Une telle position limite ainsi efficacement la recirculation d’air de l’intrados vers l’extrados.  [026] The partition is thus inclined in the direction of the direction of rotation of the blade, so as to form a deflector for the air flow. Such a position thus effectively limits the recirculation of air from the lower surface to the upper surface.
[027] Ledit angle est par exemple compris entre 30° et 60°. Said angle is for example between 30 ° and 60 °.
[028] Selon une autre caractéristique, la cloison peut être courbe, par exemple concave vue de l’intrados de la pale. According to another characteristic, the partition can be curved, for example concave viewed from the lower surface of the blade.
[029] L’invention concerne également une turbine de turbomachine comportant une roue aubagée comprenant des aubes de turbine telles que décrites précédemment.  [029] The invention also relates to a turbomachine turbine comprising a bladed wheel comprising turbine blades as described above.
[030] L’invention concerne aussi une turbomachine, telle par exemple qu’un turboréacteur d’avion, caractérisée en ce qu’elle comprend une telle turbine. The invention also relates to a turbomachine, such as for example an aircraft turbojet, characterized in that it comprises such a turbine.
[031] L’ invention sera mieux comprise et d’autres détails, caractéristiques et avantages de l’invention apparaîtront à la lecture de la description suivante faite à titre d’exemple non limitatif en référence aux dessins annexés. BREVE DESCRIPTION DES FIGURES la figure 1 est une vue schématique d’une aube de turbine de l’art antérieur ; The invention will be better understood and other details, characteristics and advantages of the invention will appear on reading the following description given by way of nonlimiting example with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE FIGURES FIG. 1 is a schematic view of a turbine blade of the prior art;
la figure 2 est une vue schématique d’un exemple de plate-forme d’aube de turbine selon une forme de réalisation de l’invention ;  FIG. 2 is a schematic view of an example of a turbine blade platform according to an embodiment of the invention;
- les figures 3A à 4B sont des vues en perspective illustrant une partie d’une aube selon différentes variantes de réalisation de l’invention. DESCRIPTION DETAILLEE - Figures 3A to 4B are perspective views illustrating part of a blade according to different embodiments of the invention. DETAILED DESCRIPTION
[032] Dans ce qui suit, les termes « amont » et « aval » sont définis par rapport au sens d’écoulement des gaz dans la turbomachine, en particulier dans la veine secondaire. De même, les termes « radial » et « axial » sont définis par rapport l’axe de la roue de turbine. Chaque aube de turbine s’étend radialement vers l’extérieur depuis le disque de la roue de turbine, dont l’axe de rotation s’étend axialement. [032] In what follows, the terms “upstream” and “downstream” are defined with respect to the direction of flow of the gases in the turbomachine, in particular in the secondary stream. Likewise, the terms "radial" and "axial" are defined relative to the axis of the turbine wheel. Each turbine blade extends radially outward from the disc of the turbine wheel, the axis of rotation of which extends axially.
[033] On se réfère ci-après aux figures 2 et suivantes en relation avec l’invention, la figure 1 , concernant la technique antérieure, ayant déjà été décrite précédemment.  Referring below to Figures 2 and following in connection with the invention, Figure 1, concerning the prior art, having already been described previously.
[034] La figure 2 illustre une partie d’une aube 13 de turbine pour une turbomachine selon l’invention. Plusieurs aubes 13 de turbine selon l’invention sont destinées à être montées sur un disque de manière à former une roue de turbine.  [034] Figure 2 illustrates part of a turbine blade 13 for a turbomachine according to the invention. Several turbine blades 13 according to the invention are intended to be mounted on a disc so as to form a turbine wheel.
[035] L’aube 13 comprend une pale 14 s’étendant radialement, et une plate- forme radialement externe 15 située au niveau de l’extrémité radialement externe de la pale 14. La pale 14 comprend un bord d’attaque 16 axialement amont et un bord de fuite axialement aval (non représenté). La plate-forme 15 comprend une extrémité amont 17 et une extrémité aval (non représentée). Ladite plate-forme 15 comporte également des léchettes, à savoir une léchette amont 18 et une léchette aval 19 dans l’exemple illustré aux figures.  The blade 13 comprises a blade 14 extending radially, and a radially external platform 15 situated at the level of the radially external end of the blade 14. The blade 14 comprises a leading edge 16 axially upstream and an axially downstream trailing edge (not shown). The platform 15 includes an upstream end 17 and a downstream end (not shown). Said platform 15 also includes wipers, namely an upstream wiper 18 and a downstream wiper 19 in the example illustrated in the figures.
[036] Dans l’exemple illustré, la plate-forme 15 s’étend axialement entre les deux léchettes 18, 19 et est ajourée par rapport à la plate-forme 5 de l’art antérieur présenté précédemment. En effet, la plate-forme 15 ne comprend pas de partie s’étendant axialement au-delà des léchettes 18,19.  In the example illustrated, the platform 15 extends axially between the two wipers 18, 19 and is perforated with respect to the platform 5 of the prior art presented previously. Indeed, the platform 15 does not include a part extending axially beyond the wipers 18,19.
[037] Une plate-forme ajourée avec une partie s’étendant au-delà des léchettes peut également être envisagée.  [037] An openwork platform with a part extending beyond the wipers can also be envisaged.
[038] Dans les deux cas, l’extrémité radialement externe 20 du bord d’attaque 16 de la pale 14 s’étend axialement vers l’amont par rapport à l’extrémité amont 17 de la plate-forme 15. De manière similaire, l’extrémité radialement externe du bord de fuite (non représentée) de la pale 14 s’étend axialement vers l’aval par rapport à l’extrémité aval de la plate-forme 15. [038] In both cases, the radially outer end 20 of the leading edge 16 of the blade 14 extends axially upstream relative to the upstream end 17 of the platform 15. Similarly, the radially outer end of the trailing edge (not shown) of the blade 14 extends axially downstream relative to the downstream end of the platform 15.
[039] L’aube 13 selon l’invention comporte en outre une cloison 21. La cloison 21 est disposée radialement à l’extérieur de l’extrémité radialement externe 20 du bord d’attaque 16 et/ou du bord de fuite (non représenté) de la pale. En effet, la cloison 21 s’étend circonférentiellement en regard de l’extrémité radialement externe 20 de la pale 14. [039] The blade 13 according to the invention further comprises a partition 21. The partition 21 is arranged radially outside the radially outer end 20 of the leading edge 16 and / or the trailing edge (not shown) of the blade. Indeed, the partition 21 extends circumferentially opposite the radially external end 20 of the blade 14.
[040] En outre, la cloison 21 s’étend axialement entre le bord d’attaque 16 et l’extrémité amont 17 de la plate-forme15, et/ou respectivement entre le bord de fuite et l’extrémité aval de la plate-forme 15.  [040] In addition, the partition 21 extends axially between the leading edge 16 and the upstream end 17 of the platform15, and / or respectively between the trailing edge and the downstream end of the platform- shape 15.
[041] La cloison 21 illustrée s’étend axialement entre le bord d’attaque 16 et une surface amont 22 de la léchette 18. De même, il est envisageable que la cloison 21 s’étende axialement entre le bord de fuite et une surface aval de la léchette.  [041] The partition 21 illustrated extends axially between the leading edge 16 and an upstream surface 22 of the wiper 18. Similarly, it is conceivable that the partition 21 extends axially between the trailing edge and a surface downstream of the wiper.
[042] Dans la forme de réalisation illustrée à la figure 2, la cloison 21 s’étend sur une partie seulement de la hauteur, c’est-à-dire la dimension radiale, de la léchette 18, 19 concernée.  [042] In the embodiment illustrated in Figure 2, the partition 21 extends over only part of the height, that is to say the radial dimension, of the wiper 18, 19 concerned.
[043] La cloison 21 comporte un bord d’extrémité 23 rectiligne et formant un angle a avec la direction radiale ou le plan radial. L’angle a est par exemple compris entre 30° et 90°. L’angle a est inscrit dans un plan ayant pour normale la direction axiale.  [043] The partition 21 has an end edge 23 rectilinear and forming an angle a with the radial direction or the radial plane. The angle a is for example between 30 ° and 90 °. The angle a is inscribed in a plane having for normal the axial direction.
[044] Plusieurs variantes de réalisation sont illustrées aux figures 3A à 4B.  [044] Several alternative embodiments are illustrated in Figures 3A to 4B.
[045] La forme géométrique et le positionnement des cloisons 21 peut varier en fonction des applications. The geometric shape and the positioning of the partitions 21 may vary depending on the applications.
[046] Dans les variantes de réalisation illustrées aux figures 3A et 4A, la cloison 21 , 27, s’étend radialement vers l’extérieur sensiblement jusqu’à l’extrémité radialement externe 24, 26 de la léchette 18, 19. En d’autres termes, la cloison 21 , 27 présente une hauteur sensiblement équivalente à celle de la léchette 18, 19. [047] De préférence, il existe un jeu de fonctionnement radial entre l’extrémité radialement externe 25 de la cloison 21 , 27 et l’extrémité radialement externe 24, 26 de la léchette 18, 19. Ce jeu de fonctionnement est par exemple compris entre 0.5 et 2 mm. [046] In the alternative embodiments illustrated in FIGS. 3A and 4A, the partition 21, 27 extends radially outwards substantially up to the radially external end 24, 26 of the wiper 18, 19. In d In other words, the partition 21, 27 has a height substantially equivalent to that of the wiper 18, 19. [047] Preferably, there is a radial operating clearance between the radially outer end 25 of the partition 21, 27 and the radially outer end 24, 26 of the wiper 18, 19. This operating clearance is for example understood between 0.5 and 2 mm.
[048] Un tel jeu permet ainsi d’éviter tout frottement de la cloison 21 , 27 sur le matériau abradable. [048] Such a play thus makes it possible to avoid any friction of the partition 21, 27 on the abradable material.
[049] Dans les variantes de réalisation illustrées aux figures 3B et 4B, la cloison 21 , 27, s’étend radialement vers l’extérieur sur une partie seulement de la dimension radiale de la léchette 18, 19.  [049] In the variant embodiments illustrated in FIGS. 3B and 4B, the partition 21, 27 extends radially outwards over only part of the radial dimension of the wiper 18, 19.
[050] En d’autres termes, l’extrémité radialement externe 25 de la cloisonIn other words, the radially outer end 25 of the partition
21 , 27 est décalée radialement vers l’intérieur par rapport à l’extrémité radialement externe 24, 26 de la Iéchette18, 19. 21, 27 is offset radially inwards relative to the radially external end 24, 26 of the Iéchette18, 19.
[051] La distance radiale entre l’extrémité radialement externe 25 de la cloison 21 , 27 et l’extrémité radialement externe 24, 26 de la léchette 18, 19 est par exemple comprise entre 0,5 mm et 2 mm.  [051] The radial distance between the radially outer end 25 of the partition 21, 27 and the radially outer end 24, 26 of the wiper 18, 19 is for example between 0.5 mm and 2 mm.
[052] Comme illustrée aux figures 3A à 4B, la cloison 21 située au niveau de la léchette 18 amont et la cloison 27 située au niveau de la léchette 19 aval peuvent s’étendre selon une direction formant un angle b avec la direction radiale.  [052] As illustrated in FIGS. 3A to 4B, the partition 21 located at the level of the upstream wiper 18 and the partition 27 located at the level of the downstream wiper 19 can extend in a direction forming an angle b with the radial direction.
[053] L’angle b est par exemple compris entre 0° et 60°. [053] The angle b is for example between 0 ° and 60 °.
[054] L’angle b est inscrit dans un plan comprenant les directions axiale et radiale.  [054] The angle b is inscribed in a plane comprising the axial and radial directions.
[055] On notera que, dans les variantes de réalisation des figures 3A à 4B, l’angle a est égal à 0.  [055] Note that, in the alternative embodiments of FIGS. 3A to 4B, the angle a is equal to 0.
[056] Dans chaque variante de réalisation des figures 3A et 3B, la cloison[056] In each variant of Figures 3A and 3B, the partition
21 amont est perpendiculaire au plan de la léchette 18 amont. 21 upstream is perpendicular to the plane of the upstream wiper 18.
[057] Par ailleurs, dans chaque variante de réalisation des figures 4A et 4B, la cloison 27 aval s’étend, au moins en partie, selon un plan formant un angle Q avec l’axe X de la turbomachine. Ainsi, la cloison et la léchette s’étendent chacune radialement en saillie de la plateforme de l’aube. En particulier, la cloison 27 aval est inclinée dans la direction du sens de rotation de l’aube R, de manière à former un déflecteur pour le flux d’air. [057] Furthermore, in each alternative embodiment of FIGS. 4A and 4B, the downstream partition 27 extends, at least in part, along a plane forming an angle Q with the axis X of the turbomachine. Thus, the partition and the wiper each extend radially projecting from the blade platform. In particular, the partition 27 downstream is inclined in the direction of the direction of rotation of the blade R, so as to form a deflector for the air flow.
[058] En d’autres termes, la cloison 27 aval est inclinée en direction de l’intrados. L’inclinaison en direction de l’intrados se révèle particulièrement intéressante car elle rend plus difficile la recirculation d’air de la zone intrados vers la zone extrados.  [058] In other words, the downstream partition 27 is inclined towards the lower surface. The inclination towards the lower surface is particularly interesting because it makes it more difficult to recirculate air from the lower surface to the upper surface.
[059] Ledit angle Q est par exemple compris entre 0° et 60°.  [059] Said angle Q is for example between 0 ° and 60 °.
[060] Dans chacune des formes de réalisation décrite précédemment, la cloison 21 , 27 constitue un obstacle à une recirculation d’air de la zone d’intrados vers la zone d’extrados, et permet ainsi de réduire les pertes liées à une telle recirculation. On augmente ainsi les performances de la turbine, tout en limitant la masse de l’aube 14 du fait des dimensions limitées de la plate-forme externe 15.  In each of the embodiments described above, the partition 21, 27 constitutes an obstacle to recirculation of air from the lower surface area to the upper surface area, and thus makes it possible to reduce the losses associated with such a recirculation. This increases the performance of the turbine, while limiting the mass of the blade 14 due to the limited dimensions of the external platform 15.

Claims

REVENDICATIONS
1. Aube (13) de turbine pour une turbomachine destinée à s’étendre autour d’un axe de la turbomachine, l’aube (13) comportant une pale (14) s’étendant radialement par rapport à l’axe entre une plateforme radialement interne (4) et une plateforme radialement externe (15), la pale (14) comprenant un bord d’attaque (16) axialement amont et un bord de fuite axialement aval, la plate-forme radialement externe (15) comprenant une extrémité amont (17) et une extrémité aval, la plate-forme radialement externe (15) comprenant au moins une léchette (18, 19) s’étendant radialement vers l’extérieur, caractérisée en ce que l’extrémité radialement externe (20) du bord d’attaque (16) de la pale (14) et/ou du bord de fuite de la pale (14) s’étendant axialement vers l’amont par rapport à l’extrémité amont (17) de la plate-forme (15) et/ou respectivement vers l’aval par rapport à l’extrémité aval de la plate-forme (15), et en ce que l’aube (13) comporte au moins une cloison (21 , 27) s’étendant radialement vers l’extérieur depuis l’extrémité radialement externe de la pale (14), et axialement entre le bord d’attaque (16) et l’extrémité amont (17) de la plate-forme (15), et/ou respectivement entre le bord de fuite et l’extrémité aval de la plate-forme (15). 1. Turbine blade (13) for a turbomachine intended to extend around an axis of the turbomachine, the blade (13) comprising a blade (14) extending radially relative to the axis between a platform radially internal (4) and a radially external platform (15), the blade (14) comprising an axially upstream leading edge (16) and an axially downstream trailing edge, the radially external platform (15) comprising an end upstream (17) and a downstream end, the radially external platform (15) comprising at least one wiper (18, 19) extending radially outwards, characterized in that the radially external end (20) of the leading edge (16) of the blade (14) and / or of the trailing edge of the blade (14) extending axially upstream relative to the upstream end (17) of the platform ( 15) and / or respectively downstream relative to the downstream end of the platform (15), and in that the blade (13) comp at least one partition (21, 27) extending radially outward from the radially outer end of the blade (14), and axially between the leading edge (16) and the upstream end (17) of the platform (15), and / or respectively between the trailing edge and the downstream end of the platform (15).
2. Aube (13) de turbine selon la revendication 1 caractérisée en ce que la cloison (21 , 27) s’étend axialement entre le bord d’attaque (16) et une surface amont (22) de la léchette (18) et/ou respectivement entre le bord de fuite et une surface aval de la léchette (19).  2. A turbine blade (13) according to claim 1 characterized in that the partition (21, 27) extends axially between the leading edge (16) and an upstream surface (22) of the wiper (18) and / or respectively between the trailing edge and a downstream surface of the wiper (19).
3. Aube (13) de turbine selon la revendication 2, caractérisée en ce que la cloison (21 , 27) s’étend radialement vers l’extérieur sensiblement jusqu’à l’extrémité radialement externe (24, 26) de la léchette (18, 19).  3. A turbine blade (13) according to claim 2, characterized in that the partition (21, 27) extends radially outwards substantially up to the radially external end (24, 26) of the wiper ( 18, 19).
4. Aube (13) de turbine selon la revendication 2, caractérisée en ce que la cloison (21 , 27) s’étend radialement vers l’extérieur sur une partie seulement de la dimension radiale de la léchette (18, 19). 4. A turbine blade (13) according to claim 2, characterized in that the partition (21, 27) extends radially outwards over only part of the radial dimension of the wiper (18, 19).
5. Aube (13) de turbine selon l’une des revendications précédentes, caractérisée en ce que la cloison (21 , 27) s’étend selon une direction formant un angle avec la direction radiale. 5. A turbine blade (13) according to one of the preceding claims, characterized in that the partition (21, 27) extends in a direction forming an angle with the radial direction.
6. Aube (13) de turbine selon l’une des revendications précédentes, caractérisée en ce que la cloison (21 , 27) comporte un bord d’extrémité amont (23) et/ou respectivement aval, rectiligne et formant un angle (a) avec la direction radiale, l’angle (a) s’inscrivant dans un plan normal à la direction axiale.  6. turbine blade (13) according to one of the preceding claims, characterized in that the partition (21, 27) has an upstream end edge (23) and / or downstream respectively, rectilinear and forming an angle (a ) with the radial direction, the angle (a) being in a plane normal to the axial direction.
7. Aube (13) de turbine selon l’une des revendications précédentes, caractérisée en ce que la léchette (18, 19) s’étend selon un plan, au moins une partie de la cloison (21 , 27) s’étendant perpendiculairement au plan de la léchette (18, 19).  7. A turbine blade (13) according to one of the preceding claims, characterized in that the wiper (18, 19) extends along a plane, at least part of the partition (21, 27) extending perpendicularly at the wiper plane (18, 19).
8. Aube (13) de turbine selon l’une des revendications 1 à 6, caractérisée en ce la léchette (18, 19) s’étend selon un plan, au moins une partie de la cloison (21 , 27) s’étendant selon un plan formant un angle (Q) avec l’axe (X) de la turbomachine.  8. A turbine blade (13) according to one of claims 1 to 6, characterized in that the wiper (18, 19) extends along a plane, at least part of the partition (21, 27) extending along a plane forming an angle (Q) with the axis (X) of the turbomachine.
9. Aube (13) de turbine selon l’une des revendications 1 à 8, caractérisé en ce que la cloison (21 , 27) est courbe, par exemple concave vue de l’intrados de la pale (14).  9. A turbine blade (13) according to one of claims 1 to 8, characterized in that the partition (21, 27) is curved, for example concave viewed from the lower surface of the blade (14).
10. Turbine de turbomachine, caractérisée en ce qu’elle comporte une roue aubagée comprenant des aubes (13) de turbine selon l’une des revendications 1 à 9.  10. Turbomachine turbine, characterized in that it comprises a bladed wheel comprising turbine blades (13) according to one of claims 1 to 9.
EP19791311.4A 2018-07-24 2019-07-23 Turbine blade Pending EP3827160A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1856854A FR3084398B1 (en) 2018-07-24 2018-07-24 TURBINE VANE
PCT/FR2019/051823 WO2020021192A1 (en) 2018-07-24 2019-07-23 Turbine blade

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CN (1) CN112513424B (en)
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WO (1) WO2020021192A1 (en)

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FR3139856A1 (en) * 2022-09-21 2024-03-22 Safran Aircraft Engines TURBOMACHINE WHEEL

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EP2439376A1 (en) * 2010-10-05 2012-04-11 Siemens Aktiengesellschaft Shrouded rotor blade for a steam turbine
FR2970999B1 (en) 2011-02-02 2015-03-06 Snecma CURRENT TURBOMACHINE AUBES, MOBILE TURBOMACHINE WHEEL AND TURBOMACHINE COMPRISING THE SAME, AND PROCESS FOR THEIR MANUFACTURE
FR2985759B1 (en) * 2012-01-17 2014-03-07 Snecma MOBILE AUB OF TURBOMACHINE
FR3001758B1 (en) * 2013-02-01 2016-07-15 Snecma TURBOMACHINE ROTOR BLADE
US9556741B2 (en) * 2014-02-13 2017-01-31 Pratt & Whitney Canada Corp Shrouded blade for a gas turbine engine
FR3027951B1 (en) * 2014-11-04 2019-12-13 Safran Aircraft Engines BATH OF SUMMIT OF DAWN OF A TURBINE OF TURBOMACHINE
US10526900B2 (en) * 2015-06-29 2020-01-07 Siemens Aktiengesellschaft Shrouded turbine blade
JP6785041B2 (en) * 2015-12-10 2020-11-18 三菱パワー株式会社 Seal structure and turbine

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CN112513424B (en) 2023-07-18
FR3084398B1 (en) 2021-04-16
US11428109B2 (en) 2022-08-30
FR3084398A1 (en) 2020-01-31
US20210262358A1 (en) 2021-08-26
WO2020021192A1 (en) 2020-01-30

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