EP3315721A1 - Leading-edge reinforcement of a turbine engine blade - Google Patents

Leading-edge reinforcement of a turbine engine blade Download PDF

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Publication number
EP3315721A1
EP3315721A1 EP17197595.6A EP17197595A EP3315721A1 EP 3315721 A1 EP3315721 A1 EP 3315721A1 EP 17197595 A EP17197595 A EP 17197595A EP 3315721 A1 EP3315721 A1 EP 3315721A1
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EP
European Patent Office
Prior art keywords
point
blade
fin
edge
radially outer
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP17197595.6A
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German (de)
French (fr)
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EP3315721B1 (en
Inventor
Jean-Louis Romero
Jean-François FREROT
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication of EP3315721A1 publication Critical patent/EP3315721A1/en
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Publication of EP3315721B1 publication Critical patent/EP3315721B1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/388—Blades characterised by 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • 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
    • F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
    • 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
    • F05D2250/711—Shape curved convex
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/133—Titanium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/174—Titanium alloys, e.g. TiAl

Definitions

  • the present invention relates to a turbomachine blade, and more particularly to a leading edge reinforcement of this blade.
  • these include a Leading edge reinforcement whose role is to protect the leading edge from deterioration during an impact with a FOD and to distribute the impact force a large area of the dawn.
  • a reinforcement of the blade leading edge conventionally comprises an extrados vane at least partially covering the aerodynamic surface of the upper surface of the vane and a vane fin at least partially covering the aerodynamic surface of the lower surface of the vane. dawn, these two fins being joined by a leading edge of the reinforcement.
  • the blade When the blade is movable relative to the axis of the turbomachine, it turns its surface intrados forward, that is to say that the air comes into contact with the surface of the lower surface thus creating an overpressure on the underside surface and a depression on its extrados surface.
  • the detachment of the extrados blade causes damage to the inner layer of abradable.
  • the extrados vane protrudes from the upper surface of the blade and penetrates into the abradable inner layer which creates a groove in the abradable inner layer. It is then necessary to immobilize the turbomachine to replace both the blade whose leading edge reinforcement has taken off and the inner layer of abradable. Such immobilization generates a significant cost resulting from the lack of exploitation of the turbomachine that it is important to reduce or even eliminate.
  • the invention aims in particular to provide a simple, effective and economical solution to this problem.
  • the invention proposes, firstly, a turbomachine blade extending along a longitudinal axis, comprising an aerodynamic surface which extends in a first direction between a leading edge and a trailing edge, and in a second direction substantially perpendicular to the first direction between a foot and a top of the blade, and a leading edge reinforcement comprising a fin partly covering the aerodynamic surface of the blade, characterized in that, the fin has a radially outer edge arranged in the vicinity of the apex of the blade and extending between the leading edge and the trailing edge, this radially outer edge comprising an upstream point flush with the top of the blade at the edge attack and a downstream point separated from the top of the dawn.
  • the upstream point is located at the upstream end of the upper edge, that is to say at the leading edge of the blade and the downstream point is located at the downstream end of the radially outer edge of the fin.
  • downstream point is spaced radially inwardly of the blade tip.
  • the aerodynamic surface is an extrados surface
  • the fin is an extrados fin, the extrados portion of the reinforcement being more particularly subject to detachment, increased separation in particular by the centrifugal force for a movable blade.
  • the radially outer edge of the fin comprises an intermediate point located between the upstream point and the downstream point and defining with the upstream point a first portion of the radially outer edge, flush with the top of the blade and, with the downstream point a second portion of the radially outer edge progressively diverging from the apex of the blade towards the vanishing point.
  • the separation into two portions offers a good compromise between limiting penetration of the fin in the abradable inner layer in case of separation of the fin, and good distribution of forces in case of impact of a FOD on the reinforcement leading edge.
  • the intermediate point may be arranged longitudinally at an equal distance from the upstream point and the downstream point.
  • the second portion of the radially outer edge of the extrados vane is curved convex. This particular shape makes it easier to manufacture the reinforcement and also to limit the creation of disturbances in the flow of the air flow.
  • This distance also offers a good compromise between limiting penetration of the fin in the abradable inner layer in case of separation of the fin, and good distribution of forces in case of impact of an FOD on the edge reinforcement. attack.
  • the reinforcement comprises a vane fin partly covering an aerodynamic surface of intrados of the blade.
  • This underside fin also helps protect the aerodynamic surface of intrados of the blade against the FOD.
  • the leading edge reinforcement is made of a metallic material.
  • the invention proposes, secondly, an assembly comprising a central disc on which are mounted a plurality of blades as previously described, said vanes being evenly distributed around the periphery of the central disc, and extending substantially radially to the disc central.
  • the invention proposes, thirdly, a turbomachine comprising an assembly as previously described.
  • a turbomachine 2 having an assembly 4 comprising a central disc 6 rotating about a longitudinal axis A of the turbomachine 2, and on which is mounted a plurality of blades 8.
  • the blades 8 are regularly distributed around the periphery 6a of the disc 6 central, and extending substantially radially to the disc 6 central.
  • the assembly 4 is the fan of the turbomachine 2
  • the blades 8 are the fan blades.
  • the turbomachine 2 also comprises, upstream to downstream, and downstream of the blower, a low pressure compressor 10, a high pressure compressor 12, a combustion chamber 14, a high pressure turbine 16, a low pressure turbine 18 , and an exhaust casing.
  • the turbomachine 2 comprises hooking means 22, in this case two, each carried by an intermediate blower housing 24 carrying an internal layer 24a abradable (visible on the figure 4 ), and a turbine casing 26.
  • radial (e) is understood to mean any direction substantially perpendicular to the axis A of the turbomachine 2, upstream the side by which the air reaches a part of the turbomachine 2, and downstream the side by which the air moves away from said part of the turbomachine 2.
  • the air flow direction is represented in FIG. figure 2 by the arrow F.
  • blade 8 is meant here both the blades 8 movable (for example the rotor blades) and the blades (for example the stator vanes) of the turbomachines 2.
  • Dawn 8 illustrated in perspective on the figure 2 and in section on the figure 3 comprises an aerodynamic surface 28 of an upper surface and an aerofoil surface 30 which extends in a first direction between a leading edge 8a and a trailing edge 8b of the blade 8.
  • the blade 8 of a fan being twisted, the first direction moves in an XY plane following the section taken in a radial direction along the Z axis which forms with the X and Y axes an orthonormal reference on the figure 2 .
  • the aerodynamic surface 28 of the upper surface and the aerodynamic surface 30 of the undersides extend between a foot 8c and an apex 8d of the blade 8.
  • the blade 8 also comprises a leading edge reinforcement 32 comprising an extrados fin 32a partly covering the aerodynamic surface 28 of the extrados of the substantially radial blade 8, and a fin 29b of a lower surface covering part of the airfoil. aerodynamic surface of the underside of the blade 8.
  • These two fins 32a, 32b have, as visible in FIG. figure 3 , a section that is refined from upstream to downstream.
  • the two fins 32a, 32b are joined by a leading edge 32c which covers the leading edge 8a of the blade 8 and has, in section, a thickness greater than the maximum thickness of the fins 32a, 32b.
  • the reinforcement 32 of edge 8a of attack of the blade 8 extends substantially from the foot 8c of the blade 8, to its top 8d.
  • the leading edge reinforcement 32 is preferably made of a highly resistant metallic material, such as, for example, a titanium alloy.
  • the detail view of the figure 4 highlights a particularity of the fin 32a of extrados of the leading edge reinforcement 32.
  • the extrados vane 32a has a radially outer (also upper) edge 34 arranged in the vicinity of the blade crown 8d and which extends from the leading edge 8a to the edge 8b ( figure 2 ) leak.
  • This radially outer edge 34 comprises an upstream point 34a which is flush with the apex 8d of the blade 8 at the leading edge 8a and a downstream point 34b which is spaced from the apex 8d of the blade 8.
  • the term "superior" according to the orientation of the figure 4 .
  • the radially outer edge 34 is disposed radially outwardly with respect to the axis A of the turbomachine 2.
  • upstream point 34a is arranged on the side of the leading edge 8a of the blade 8 and the downstream point 34b is arranged on the side of the trailing edge 8b of the blade 8 in the direction of air flow.
  • F figure 2
  • the upper radially outer edge 34 of the extrados fin 32a comprises an intermediate point 34c situated between the upstream point 34a and the downstream point 34b and defining, with the upstream point 34a, a first portion 36 of the radially outer edge flush with the top 8d of the blade 8 and, with the point 34b downstream, a second portion 38 of the upper edge progressively diverging from the top 8d of the blade 8.
  • the connection of the first portion 36 of the radially outer edge 34 with the second portion 38 of the upper edge is substantially tangential.
  • the intermediate point 34c is arranged equidistant from the upstream point 34a and the downstream point 34b, in an axial direction parallel to the longitudinal axis A.
  • intermediate point 34c could be closer to point 34a upstream or point 34b downstream.
  • a fictitious extreme point 34e corresponding to the symmetry of the point 34a upstream with respect to a median axis M substantially perpendicular to the axis A of the turbomachine 2, and passing at least through the center of the top of the fin 32a of extrados .
  • This 34th point fictitious extreme corresponds to an extreme point of the fin 32a extrados before optimization of the latter.
  • this point 34th extreme makes it possible to define the progressive spacing of the point 34b downstream from the vertex 8d of the blade 8.
  • the spacing of the second portion 38 of the radially outer edge 34 of the extrados fin 32a is preferably convexly curved.
  • the second portion 38 has a substantially curved shape that moves away from the top 8d of the blade 8 in the direction of the foot 8c ( figure 2 ) of the latter, and this upstream downstream.
  • the second portion 38 of the radially outer edge 34 of the extrados vane 32a could be rectilinear or, conversely, comprise an alternation of bumps and depressions.
  • the distance L, the tangent T and the angle ⁇ are illustrated on the figure 5 .
  • the lower surface fin 32b also comprises an upper edge having an upstream point flush with the apex 8d of the blade 8 and a downstream point remote from the upstream point and spaced from the vertex 8d of the blade 8, that is to say radially distant internally.
  • the upper edge of the lower surface fin 32b may also comprise an intermediate point situated between the point of attack and the vanishing point and defining with the point of attack a first portion of the upper edge, flush with the top 8d of the dawn 8 and, with the vanishing point, a second portion of the upper edge progressively diverging from the apex 8d of the blade 8 towards the foot 8c.
  • the shapes and dimensions of the portions of the vane fin 32b are reduced with respect to the shapes and dimensions of the portions 36, 38 of the upper edge 34 of the extrados vane 32a.

Abstract

L'invention concerne une aube de turbomachine, comprenant une surface (28) aérodynamique qui s'étend selon une première direction entre un bord (8a) d'attaque et un bord de fuite, et selon une deuxième direction sensiblement perpendiculaire à la première direction entre un pied et un sommet (8d) de l'aube, et un renfort (32) de bord d'attaque comprenant une ailette (32a) recouvrant en partie la surface aérodynamique (28) de l'aube, caractérisée en ce que, l'ailette (32a) présente un bord (34) radialement extérieur agencé au voisinage du sommet (8d) de l'aube et s'étendant entre le bord (8a) d'attaque et le bord de fuite, ce bord (34) radialement extérieur comprenant un point (34a) amont affleurant le sommet (8d) de l'aube au niveau du bord (8a) d'attaque et un point (34b) dit aval écarté du sommet (8d) de l'aube.The invention relates to a turbomachine blade, comprising an aerodynamic surface (28) extending in a first direction between a leading edge (8a) and a trailing edge, and in a second direction substantially perpendicular to the first direction between a root and a top (8d) of the blade, and a leading edge reinforcement (32) comprising a fin (32a) partially covering the aerodynamic surface (28) of the blade, characterized in that, the fin (32a) has a radially outer edge (34) arranged in the vicinity of the apex (8d) of the blade and extending between the leading edge (8a) and the trailing edge, this edge (34) radially outer comprising an upstream point (34a) flush with the apex (8d) of the blade at the edge (8a) of attack and a point (34b) said downstream spaced from the vertex (8d) of the blade.

Description

La présente invention concerne une aube de turbomachine, et plus particulièrement un renfort de bord d'attaque de cette aube.The present invention relates to a turbomachine blade, and more particularly to a leading edge reinforcement of this blade.

Par aube on entend ici à la fois les aubes mobiles et les aubes fixes des turbomachines.By dawn means here both the blades and the blades of the turbomachines.

Afin d'augmenter la résistance des aubes aux FOD (acronyme de l'anglais Foreign Object Damages) dans le flux d'air, c'est-à-dire aux corps étrangers tels que les oiseaux ou les grêlons, celles-ci comprennent un renfort de bord d'attaque dont le rôle est de protéger le bord d'attaque d'une détérioration lors d'un impact avec un FOD et de répartir l'effort de l'impact une grande surface de l'aube.In order to increase the resistance of the blades to the Foreign Object Damages (FOD) in the airflow, that is to say to foreign bodies such as birds or hailstones, these include a Leading edge reinforcement whose role is to protect the leading edge from deterioration during an impact with a FOD and to distribute the impact force a large area of the dawn.

Un renfort du bord d'attaque d'aube comprend classiquement une ailette d'extrados recouvrant au moins partiellement la surface aérodynamique d'extrados de l'aube et une ailette d'intrados recouvrant au moins partiellement la surface aérodynamique d'intrados de l'aube, ces deux ailettes étant jointes par un bord d'attaque du renfort.A reinforcement of the blade leading edge conventionally comprises an extrados vane at least partially covering the aerodynamic surface of the upper surface of the vane and a vane fin at least partially covering the aerodynamic surface of the lower surface of the vane. dawn, these two fins being joined by a leading edge of the reinforcement.

Lorsque l'aube est mobile par rapport à l'axe de la turbomachine, elle tourne sa surface d'intrados en avant, c'est-à-dire que l'air vient au contact sur la surface d'intrados créant ainsi une surpression sur la surface d'intrados et une dépression sur sa surface d'extrados.When the blade is movable relative to the axis of the turbomachine, it turns its surface intrados forward, that is to say that the air comes into contact with the surface of the lower surface thus creating an overpressure on the underside surface and a depression on its extrados surface.

L'impact d'un FOD sur le renfort de bord d'attaque a tendance à provoquer un décollement de la portion supérieure de l'ailette d'intrados. Au-delà d'une certaine masse des FOD, la force des impacts est plus importante sur le renfort, ce qui provoque également un décollement de la portion supérieure de l'ailette d'extrados. La surpression générée sur la surface d'intrados tend à limiter le décollement de l'ailette d'intrados à la surface d'intrados. En revanche la combinaison de la force centrifuge, plus importante en sommet d'aube qu'en pied, avec la dépression générée sur la surface d'extrados, tend à favoriser le décollement de l'ailette d'extrados.The impact of a FOD on the leading edge reinforcement tends to cause a detachment of the upper portion of the intrados vane. Beyond a certain mass of the FOD, the force of the impacts is greater on the reinforcement, which also causes a detachment of the upper portion of the extrados fin. The overpressure generated on the intrados surface tends to limit the detachment of the intrados vane to the intrados surface. On the other hand, the combination of the centrifugal force, more important at the top of the blade than at the bottom, with the depression generated on the extrados surface, tends to favor the separation of the extrados vane.

Lorsque l'aube est une aube de soufflante montée dans un carénage externe portant une couche interne d'abradable en regard des aubes, le décollement de l'ailette d'extrados provoque un endommagement de la couche interne d'abradable. En effet, l'ailette d'extrados fait saillie de la surface d'extrados de l'aube et pénètre dans la couche interne d'abradable ce qui crée un sillon dans la couche interne d'abradable. Il est alors nécessaire d'immobiliser la turbomachine pour remplacer à la fois l'aube dont le renfort de bord d'attaque s'est décollé et la couche interne d'abradable. Une telle immobilisation génère un coût important résultant du manque d'exploitation de la turbomachine qu'il est important de réduire, voire de supprimer.When the blade is a blade of a fan mounted in an external fairing bearing an internal layer of abradable facing the blades, the detachment of the extrados blade causes damage to the inner layer of abradable. Indeed, the extrados vane protrudes from the upper surface of the blade and penetrates into the abradable inner layer which creates a groove in the abradable inner layer. It is then necessary to immobilize the turbomachine to replace both the blade whose leading edge reinforcement has taken off and the inner layer of abradable. Such immobilization generates a significant cost resulting from the lack of exploitation of the turbomachine that it is important to reduce or even eliminate.

L'invention a notamment pour but d'apporter une solution simple, efficace et économique à ce problème.The invention aims in particular to provide a simple, effective and economical solution to this problem.

A cet effet, l'invention propose, en premier lieu, une aube de turbomachine s'étendant suivant un axe longitudinal, comprenant une surface aérodynamique qui s'étend selon une première direction entre un bord d'attaque et un bord de fuite, et selon une deuxième direction sensiblement perpendiculaire à la première direction entre un pied et un sommet de l'aube, et un renfort de bord d'attaque comprenant une ailette recouvrant en partie la surface aérodynamique de l'aube, caractérisée en ce que, l'ailette présente un bord radialement extérieur agencé au voisinage du sommet de l'aube et s'étendant entre le bord d'attaque et le bord de fuite, ce bord radialement extérieur comprenant un point amont affleurant le sommet de l'aube au niveau du bord d'attaque et un point aval écarté du sommet de l'aube.For this purpose, the invention proposes, firstly, a turbomachine blade extending along a longitudinal axis, comprising an aerodynamic surface which extends in a first direction between a leading edge and a trailing edge, and in a second direction substantially perpendicular to the first direction between a foot and a top of the blade, and a leading edge reinforcement comprising a fin partly covering the aerodynamic surface of the blade, characterized in that, the fin has a radially outer edge arranged in the vicinity of the apex of the blade and extending between the leading edge and the trailing edge, this radially outer edge comprising an upstream point flush with the top of the blade at the edge attack and a downstream point separated from the top of the dawn.

L'écartement du point aval du bord supérieur de l'ailette d'extrados permet de limiter la pénétration de l'ailette dans la couche interne d'abradable de la turbomachine, en cas de décollement du point aval de l'aube puisque celui-ci se retrouve alors éloigné de l'abradable du fait de son éloignement au montage du sommet d'aube.The spacing of the downstream point from the upper edge of the extrados vane makes it possible to limit the penetration of the vane into the abradable inner layer of the turbomachine, in case of detachment from the downstream point of the vane since this It is then removed from the abradable because of its remoteness at the mounting of the dawn apex.

Dans une réalisation particulière de l'invention, le point amont est situé au niveau de l'extrémité amont du bord supérieur, c'est-à-dire au niveau du bord d'attaque de l'aube et le point aval est situé à l'extrémité aval du bord radialement extérieur de l'ailette.In a particular embodiment of the invention, the upstream point is located at the upstream end of the upper edge, that is to say at the leading edge of the blade and the downstream point is located at the downstream end of the radially outer edge of the fin.

Dans le repère de la turbomachine, on peut ainsi considérer que le point aval est écarté radialement vers l'intérieur du sommet d'aube.In the reference of the turbomachine, it can thus be considered that the downstream point is spaced radially inwardly of the blade tip.

Avantageusement, la surface aérodynamique est une surface d'extrados, et l'ailette est une ailette d'extrados, la partie extrados du renfort étant plus particulièrement sujette au décollement, décollement accru notamment par la force centrifuge pour une pale mobile.Advantageously, the aerodynamic surface is an extrados surface, and the fin is an extrados fin, the extrados portion of the reinforcement being more particularly subject to detachment, increased separation in particular by the centrifugal force for a movable blade.

Avantageusement, le bord radialement extérieur de l'ailette comprend un point intermédiaire situé entre le point amont et le point aval et définissant avec le point amont une première portion du bord radialement extérieur, affleurant le sommet de l'aube et, avec le point aval, une seconde portion du bord radialement extérieur s'écartant progressivement du sommet de l'aube en direction du point de fuite.Advantageously, the radially outer edge of the fin comprises an intermediate point located between the upstream point and the downstream point and defining with the upstream point a first portion of the radially outer edge, flush with the top of the blade and, with the downstream point a second portion of the radially outer edge progressively diverging from the apex of the blade towards the vanishing point.

La séparation en deux portions offre un bon compromis entre limitation de pénétration de l'ailette dans la couche interne d'abradable en cas de décollement de l'ailette, et bonne répartition des efforts en cas d'impact d'un FOD sur le renfort de bord d'attaque.The separation into two portions offers a good compromise between limiting penetration of the fin in the abradable inner layer in case of separation of the fin, and good distribution of forces in case of impact of a FOD on the reinforcement leading edge.

Le point intermédiaire peut être agencé longitudinalement à égale distance du point amont et du point aval.The intermediate point may be arranged longitudinally at an equal distance from the upstream point and the downstream point.

Cela permet de protéger l'aube sur toute la hauteur puisque la première portion affleure avec le sommet de l'aube.This protects the dawn all the way up since the first portion is flush with the top of the dawn.

De préférence, la seconde portion du bord radialement extérieur de l'ailette extrados est incurvée convexe. Cette forme particulière permet de faciliter la fabrication du renfort et, également, de limiter la création de perturbations dans l'écoulement du flux d'air.Preferably, the second portion of the radially outer edge of the extrados vane is curved convex. This particular shape makes it easier to manufacture the reinforcement and also to limit the creation of disturbances in the flow of the air flow.

Avantageusement, le point intermédiaire et le point de fuite sont séparés l'un de l'autre d'une distance, mesurée le long d'un axe longitudinal médian de l'ailette, comprise entre 0 et sinα × L ÷ 4 où :

  • L est la longueur de l'ailette avant optimisation, c'est-à-dire entre le point amont et un point extrême fictif correspondant à la symétrie du point amont par rapport à l'axe médian sensiblement perpendiculaire à l'axe longitudinal de la turbomachine, et passant au moins par le centre du sommet de l'ailette, et
  • α est l'angle mesuré entre une ligne passant par le point amont et le point intermédiaire du bord radialement extérieur et une tangente au bord radialement extérieur, parallèle à l'axe longitudinal et passant par le point intermédiaire.
Advantageously, the intermediate point and the vanishing point are separated from one another by a distance, measured along a median longitudinal axis of the fin, between 0 and sinα × L ÷ 4 or :
  • L is the length of the fin before optimization, that is to say between the upstream point and a fictive extreme point corresponding to the symmetry of the upstream point relative to the median axis substantially perpendicular to the longitudinal axis of the turbomachine, and passing at least through the center of the top of the fin, and
  • α is the angle measured between a line passing through the upstream point and the intermediate point of the radially outer edge and a tangent to the radially outer edge, parallel to the longitudinal axis and passing through the intermediate point.

Cette distance offre également un bon compromis entre limitation de pénétration de l'ailette dans la couche interne d'abradable en cas de décollement de l'ailette, et bonne répartition des efforts en cas d'impact d'un FOD sur le renfort de bord d'attaque.This distance also offers a good compromise between limiting penetration of the fin in the abradable inner layer in case of separation of the fin, and good distribution of forces in case of impact of an FOD on the edge reinforcement. attack.

De préférence, le renfort comprend une ailette d'intrados recouvrant en partie une surface aérodynamique d'intrados de l'aube.Preferably, the reinforcement comprises a vane fin partly covering an aerodynamic surface of intrados of the blade.

Cette ailette d'intrados permet également de protéger la surface aérodynamique d'intrados de l'aube contre les FOD.This underside fin also helps protect the aerodynamic surface of intrados of the blade against the FOD.

Pour assurer une bonne protection de l'aube, le renfort de bord d'attaque est réalisé dans un matériau métallique.To ensure good protection of the blade, the leading edge reinforcement is made of a metallic material.

L'invention propose, en deuxième lieu, un ensemble comprenant un disque central sur lequel sont montées une pluralité d'aubes telles que précédemment décrites, lesdites aubes étant régulièrement réparties autour de la périphérie du disque central, et s'étendant sensiblement radialement au disque central.The invention proposes, secondly, an assembly comprising a central disc on which are mounted a plurality of blades as previously described, said vanes being evenly distributed around the periphery of the central disc, and extending substantially radially to the disc central.

L'invention propose, en troisième lieu, une turbomachine comprenant un ensemble tel que précédemment décrit.The invention proposes, thirdly, a turbomachine comprising an assembly as previously described.

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 dans lesquels :

  • la figure 1 est une vue schématique d'une turbomachine comprenant un ensemble ayant une pluralité d'aubes;
  • la figure 2 est une vue en perspective d'une aube selon l'invention, en particulier une aube de soufflante, cette aube portant un renfort de bord d'attaque limitant la dégradation de la couche interne d'abradable de la turbomachine ;
  • la figure 3 est une vue en section de l'aube selon le plan de section III - III de la figure 2 ;
  • la figure 4 est une vue de détail d'une portion supérieure de l'aube selon l'encart IV de la figure 2, et
  • la figure 5 est une vue de détail à échelle agrandie du détail V de la figure 4.
The invention will be better understood and other details, features and advantages of the invention will become apparent on reading the following description given by way of non-limiting example with reference to the accompanying drawings in which:
  • the figure 1 is a schematic view of a turbomachine comprising an assembly having a plurality of blades;
  • the figure 2 is a perspective view of a blade according to the invention, in particular a fan blade, this blade carrying a leading edge reinforcement limiting the degradation of the inner abradable layer of the turbomachine;
  • the figure 3 is a sectional view of the dawn according to the section III - III plan of the figure 2 ;
  • the figure 4 is a detail view of an upper portion of dawn according to inset IV of the figure 2 , and
  • the figure 5 is an enlarged detail view of detail V of the figure 4 .

On a représenté, sur la figure 1, une turbomachine 2 ayant un ensemble 4 comprenant un disque 6 central rotatif autour d'un axe longitudinal A de la turbomachine 2, et sur lequel est montée une pluralité d'aubes 8. Les aubes 8 sont régulièrement réparties autour de la périphérie 6a du disque 6 central, et s'étendant sensiblement radialement au disque 6 central. Dans le cas présent, l'ensemble 4 est la soufflante de la turbomachine 2, et les aubes 8 sont les aubes de soufflante.On the figure 1 , a turbomachine 2 having an assembly 4 comprising a central disc 6 rotating about a longitudinal axis A of the turbomachine 2, and on which is mounted a plurality of blades 8. The blades 8 are regularly distributed around the periphery 6a of the disc 6 central, and extending substantially radially to the disc 6 central. In this case, the assembly 4 is the fan of the turbomachine 2, and the blades 8 are the fan blades.

Classiquement, la turbomachine 2 comprend également, d'amont en aval, et en aval de la soufflante, un compresseur 10 basse pression, un compresseur 12 haute pression, une chambre 14 de combustion, une turbine 16 haute pression, une turbine 18 basse pression, et un carter 20 d'échappement. En outre, pour son accrochage à l'avion, la turbomachine 2 comprend des moyens 22 d'accrochage, en l'espèce deux, portés chacun par un carter 24 intermédiaire de soufflante portant une couche 24a interne d'abradable (visible sur la figure 4), et un carter 26 de turbine.Conventionally, the turbomachine 2 also comprises, upstream to downstream, and downstream of the blower, a low pressure compressor 10, a high pressure compressor 12, a combustion chamber 14, a high pressure turbine 16, a low pressure turbine 18 , and an exhaust casing. In addition, for its attachment to the aircraft, the turbomachine 2 comprises hooking means 22, in this case two, each carried by an intermediate blower housing 24 carrying an internal layer 24a abradable (visible on the figure 4 ), and a turbine casing 26.

Dans la suite de cette description on entend par le terme radial(e) toute direction sensiblement perpendiculaire à l'axe A de la turbomachine 2, par amont le côté par lequel l'air atteint une pièce de la turbomachine 2, et par aval le côté par lequel l'air s'éloigne de ladite pièce de la turbomachine 2. La direction d'écoulement d'air est représentée en figure 2 par la flèche F.In the remainder of this description, the term radial (e) is understood to mean any direction substantially perpendicular to the axis A of the turbomachine 2, upstream the side by which the air reaches a part of the turbomachine 2, and downstream the side by which the air moves away from said part of the turbomachine 2. The air flow direction is represented in FIG. figure 2 by the arrow F.

Par aube 8, on entend ici à la fois les aubes 8 mobiles (par exemple les aubes de rotor) et les aubes fixes (par exemple les aubes de stator) des turbomachines 2.By blade 8, is meant here both the blades 8 movable (for example the rotor blades) and the blades (for example the stator vanes) of the turbomachines 2.

L'aube 8, illustrée en perspective sur la figure 2 et en section sur la figure 3, comprend une surface 28 aérodynamique d'extrados et une surface 30 aérodynamique d'intrados qui s'étendent selon une première direction entre un bord 8a d'attaque et un bord 8b de fuite de l'aube 8. L'aube 8 d'une soufflante étant vrillée, la première direction évolue dans un plan XY suivant la section prise dans une direction radiale suivant l'axe Z qui forme avec les axes X et Y un repère orthonormé sur la figure 2. Selon une deuxième direction sensiblement perpendiculaire à la première direction, la surface 28 aérodynamique d'extrados et la surface 30 aérodynamique d'intrados s'étendent entre un pied 8c et un sommet 8d de l'aube 8.Dawn 8, illustrated in perspective on the figure 2 and in section on the figure 3 comprises an aerodynamic surface 28 of an upper surface and an aerofoil surface 30 which extends in a first direction between a leading edge 8a and a trailing edge 8b of the blade 8. The blade 8 of a fan being twisted, the first direction moves in an XY plane following the section taken in a radial direction along the Z axis which forms with the X and Y axes an orthonormal reference on the figure 2 . In a second direction substantially perpendicular to the first direction, the aerodynamic surface 28 of the upper surface and the aerodynamic surface 30 of the undersides extend between a foot 8c and an apex 8d of the blade 8.

L'aube 8 comprend également un renfort 32 de bord d'attaque comprenant une ailette 32a d'extrados recouvrant en partie la surface 28 aérodynamique d'extrados de l'aube 8 sensiblement radiale, et une ailette 32b d'intrados recouvrant en partie la surface 30 aérodynamique d'intrados de l'aube 8. Ces deux ailettes 32a, 32b présentent, comme visible en figure 3, une section qui va en s'affinant depuis l'amont vers l'aval.The blade 8 also comprises a leading edge reinforcement 32 comprising an extrados fin 32a partly covering the aerodynamic surface 28 of the extrados of the substantially radial blade 8, and a fin 29b of a lower surface covering part of the airfoil. aerodynamic surface of the underside of the blade 8. These two fins 32a, 32b have, as visible in FIG. figure 3 , a section that is refined from upstream to downstream.

Les deux ailettes 32a, 32b sont jointes par un bord 32c d'attaque qui recouvre le bord 8a d'attaque de l'aube 8 et présente, en section, une épaisseur supérieure à l'épaisseur maximale des ailettes 32a, 32b.The two fins 32a, 32b are joined by a leading edge 32c which covers the leading edge 8a of the blade 8 and has, in section, a thickness greater than the maximum thickness of the fins 32a, 32b.

Comme on le voit sur la figure 2, le renfort 32 de bord 8a d'attaque de l'aube 8 s'étend sensiblement depuis le pied 8c de l'aube 8, jusqu'à son sommet 8d.As we see on the figure 2 , the reinforcement 32 of edge 8a of attack of the blade 8 extends substantially from the foot 8c of the blade 8, to its top 8d.

Le renfort 32 de bord d'attaque est, de préférence, réalisé dans un matériau métallique hautement résistant, tel que par exemple un alliage de titane.The leading edge reinforcement 32 is preferably made of a highly resistant metallic material, such as, for example, a titanium alloy.

La vue de détail de la figure 4 met en avant une particularité de l'ailette 32a d'extrados du renfort 32 de bord d'attaque. En effet, l'ailette 32a d'extrados présente un bord 34 radialement extérieur (également dit supérieur) agencé au voisinage du sommet 8d d'aube et qui s'étend depuis le bord 8a d'attaque vers le bord 8b (figure 2) de fuite. Ce bord 34 radialement extérieur comprend un point 34a amont qui affleure le sommet 8d de l'aube 8 au niveau du bord 8a d'attaque et un point 34b aval qui est écarté du sommet 8d de l'aube 8. Le terme « supérieur » s'entend selon l'orientation de la figure 4. Autrement dit le bord 34 radialement extérieur est disposé radialement extérieurement par rapport à l'axe A de la turbomachine 2.The detail view of the figure 4 highlights a particularity of the fin 32a of extrados of the leading edge reinforcement 32. Indeed, the extrados vane 32a has a radially outer (also upper) edge 34 arranged in the vicinity of the blade crown 8d and which extends from the leading edge 8a to the edge 8b ( figure 2 ) leak. This radially outer edge 34 comprises an upstream point 34a which is flush with the apex 8d of the blade 8 at the leading edge 8a and a downstream point 34b which is spaced from the apex 8d of the blade 8. The term "superior" according to the orientation of the figure 4 . In other words, the radially outer edge 34 is disposed radially outwardly with respect to the axis A of the turbomachine 2.

On comprendra que le point 34a amont est agencé du côté du bord 8a d'attaque de l'aube 8 et le point 34b aval est agencé du côté du bord 8b de fuite de l'aube 8 selon la direction d'écoulement d'air F (figure 2) sur l'aube 8 depuis le bord 8a d'attaque vers le bord 8b de fuite.It will be understood that the upstream point 34a is arranged on the side of the leading edge 8a of the blade 8 and the downstream point 34b is arranged on the side of the trailing edge 8b of the blade 8 in the direction of air flow. F ( figure 2 ) on the blade 8 from the leading edge 8a to the trailing edge 8b.

En outre, le bord 34 radialement extérieur supérieur de l'ailette 32a d'extrados comprend un point 34c intermédiaire situé entre le point 34a amont et le point 34b aval et définissant avec le point 34a amont une première portion 36 du bord radialement extérieur, affleurant le sommet 8d de l'aube 8 et, avec le point 34b aval, une seconde portion 38 du bord supérieur s'écartant progressivement du sommet 8d de l'aube 8. Le raccordement de la première portion 36 du bord 34 radialement extérieur avec la seconde portion 38 du bord supérieur est sensiblement tangentiel.In addition, the upper radially outer edge 34 of the extrados fin 32a comprises an intermediate point 34c situated between the upstream point 34a and the downstream point 34b and defining, with the upstream point 34a, a first portion 36 of the radially outer edge flush with the top 8d of the blade 8 and, with the point 34b downstream, a second portion 38 of the upper edge progressively diverging from the top 8d of the blade 8. The connection of the first portion 36 of the radially outer edge 34 with the second portion 38 of the upper edge is substantially tangential.

Selon un aspect, le point 34c intermédiaire est agencé à égale distance du point 34a amont et du point 34b aval, selon une direction axiale parallèle à l'axe A longitudinal. Toutefois, le point 34c intermédiaire pourrait être plus proche du point 34a amont ou du point 34b aval.In one aspect, the intermediate point 34c is arranged equidistant from the upstream point 34a and the downstream point 34b, in an axial direction parallel to the longitudinal axis A. However, intermediate point 34c could be closer to point 34a upstream or point 34b downstream.

On a représenté sur la figure 5, un point 34e extrême fictif correspondant à la symétrie du point 34a amont par rapport à un axe médian M sensiblement perpendiculaire à l'axe A de la turbomachine 2, et passant au moins par le centre du sommet de l'ailette 32a d'extrados. Ce point 34e extrême fictif correspond à un point extrême de l'ailette 32a d'extrados avant optimisation de cette dernière.We have shown on the figure 5 , a fictitious extreme point 34e corresponding to the symmetry of the point 34a upstream with respect to a median axis M substantially perpendicular to the axis A of the turbomachine 2, and passing at least through the center of the top of the fin 32a of extrados . This 34th point fictitious extreme corresponds to an extreme point of the fin 32a extrados before optimization of the latter.

Avantageusement, ce point 34e extrême permet de définir l'écartement progressif du point 34b aval par rapport au sommet 8d de l'aube 8.Advantageously, this point 34th extreme makes it possible to define the progressive spacing of the point 34b downstream from the vertex 8d of the blade 8.

L'écartement de la seconde portion 38 du bord 34 radialement extérieur de l'ailette 32a extrados est de préférence incurvée convexe. Autrement dit, la seconde portion 38 a sensiblement une forme courbe qui s'écarte de manière continue du sommet 8d de l'aube 8 en direction du pied 8c (figure 2) de cette dernière, et ceci d'amont en aval.The spacing of the second portion 38 of the radially outer edge 34 of the extrados fin 32a is preferably convexly curved. In other words, the second portion 38 has a substantially curved shape that moves away from the top 8d of the blade 8 in the direction of the foot 8c ( figure 2 ) of the latter, and this upstream downstream.

Toutefois, selon des variantes de réalisation non représentées sur les figures, la seconde portion 38 du bord 34 radialement extérieur de l'ailette 32a d'extrados pourrait être rectiligne ou, au contraire, comprendre une alternance de bosses et de creux.However, according to alternative embodiments not shown in the figures, the second portion 38 of the radially outer edge 34 of the extrados vane 32a could be rectilinear or, conversely, comprise an alternation of bumps and depressions.

Selon un mode préféré de réalisation représenté à la figure 5, le point 34c intermédiaire et le point 34b aval sont séparés l'un de l'autre d'une distance H1 mesurée le long de l'axe M longitudinal médian , c'est-à-dire suivant la direction radiale Z, H1 étant comprise entre 0 et sinα × L ÷ 4 où :

  • L est la longueur de l'ailette 32a avant optimisation, c'est-à-dire entre le point 34a amont et le point 34e fictif, et
  • α est l'angle mesuré entre une ligne passant par le point 34a amont et le point 34c intermédiaire du bord 34 radialement extérieur et une tangente T audit bord 34 radialement extérieur, parallèle à l'axe longitudinal A de la turbomachine 2 et passant par le point 34 c intermédiaire.
According to a preferred embodiment represented at figure 5 the intermediate point 34c and the downstream point 34b are separated from each other by a distance H1 measured along the median longitudinal axis M, that is to say in the radial direction Z, H1 being between 0 and sinα × L ÷ 4 where:
  • L is the length of the fin 32a before optimization, that is to say between the point 34a upstream and the point 34e fictitious, and
  • α is the angle measured between a line passing through the point 34a upstream and the intermediate point 34c of the radially outer edge 34 and a tangent T to said radially outer edge 34, parallel to the longitudinal axis A of the turbomachine 2 and passing through the point 34c intermediate.

La distance L, la tangente T et l'angle α sont illustrés sur la figure 5.The distance L, the tangent T and the angle α are illustrated on the figure 5 .

Ainsi, en cas d'impact d'un FOD sur le renfort 32 de bord d'attaque, si l'ailette 32a d'extrados vient à se décoller, elle ne rentrera pas en contact avec la couche 24a interne d'abradable portée par le carter 24 intermédiaire de soufflante. Dès lors, il ne sera nécessaire que de réparer l'aube 8 qui a été impactée (ou les aubes 8 impactées), ce qui est plus simple, plus rapide et moins onéreux que l'immobilisation complète de la turbomachine 2 pour le remplacement de l'aube 8 impactée (ou des aubes 8 impactées) et du carter 24 intermédiaire de soufflante et de sa couche 24a interne d'abradable.Thus, in the event of an impact of an FOD on the leading edge reinforcement 32, if the upper winglet 32a comes off, it will not come into contact with the abradable inner layer 24a carried by the housing 24 intermediate blower. Therefore, it will only be necessary to repair the blade 8 which has been impacted (or the blades 8 impacted), which is simpler, faster and less expensive than the complete immobilization of the turbomachine 2 for the replacement of the impacted blade 8 (or impacted blades 8) and the intermediate fan casing 24 and its abradable internal layer 24a.

Pour des raisons de simplicité de fabrication du renfort 32 de bord d'attaque, l'ailette 32b d'intrados comprend également un bord supérieur ayant un point amont affleurant le sommet 8d de l'aube 8 et un point aval distant du point amont et écarté du sommet 8d de l'aube 8, c'est-à-dire distant radialement intérieurement.For the sake of simplicity of manufacture of the leading edge reinforcement 32, the lower surface fin 32b also comprises an upper edge having an upstream point flush with the apex 8d of the blade 8 and a downstream point remote from the upstream point and spaced from the vertex 8d of the blade 8, that is to say radially distant internally.

Le bord supérieur de l'ailette 32b d'intrados peut également comprendre un point intermédiaire situé entre le point d'attaque et le point de fuite et définissant avec le point d'attaque une première portion du bord supérieur, affleurant le sommet 8d de l'aube 8 et, avec le point de fuite, une seconde portion du bord supérieur s'écartant progressivement du sommet 8d de l'aube 8 en direction du pied 8c.The upper edge of the lower surface fin 32b may also comprise an intermediate point situated between the point of attack and the vanishing point and defining with the point of attack a first portion of the upper edge, flush with the top 8d of the dawn 8 and, with the vanishing point, a second portion of the upper edge progressively diverging from the apex 8d of the blade 8 towards the foot 8c.

Toutefois, les formes et les dimensions des portions de l'ailette 32b d'intrados sont réduites par rapport aux formes et aux dimensions des portions 36, 38 du bord 34 supérieur de l'ailette 32a d'extrados.However, the shapes and dimensions of the portions of the vane fin 32b are reduced with respect to the shapes and dimensions of the portions 36, 38 of the upper edge 34 of the extrados vane 32a.

Ainsi, on obtiendra un renfort 32 dissymétrique.Thus, an asymmetrical reinforcement 32 will be obtained.

Claims (10)

Aube (8) de turbomachine s'étendant suivant un axe longitudinal (A), comprenant une surface (28, 30) aérodynamique qui s'étend selon une première direction entre un bord (8a) d'attaque et un bord (8b) de fuite, et selon une deuxième direction sensiblement perpendiculaire à la première direction entre un pied (8c) et un sommet (8d) de l'aube (8), et un renfort (32) de bord d'attaque comprenant une ailette (32a, 32b) recouvrant en partie la surface aérodynamique (28, 30) de l'aube (8), caractérisée en ce que, l'ailette (32a, 32b) présente un bord (34) radialement extérieur agencé au voisinage du sommet (8d) de l'aube (8) et s'étendant entre le bord (8a) d'attaque et le bord (8b) de fuite, ce bord (34) radialement extérieur comprenant un point (34a) amont affleurant le sommet (8d) de l'aube (8) au niveau du bord d'attaque et un point (34b) aval distant radialement du sommet (8d) de l'aube (8).A turbomachine blade (8) extending along a longitudinal axis (A), comprising an aerodynamic surface (28, 30) extending in a first direction between a leading edge (8a) and an edge (8b) of leak, and in a second direction substantially perpendicular to the first direction between a foot (8c) and a vertex (8d) of the blade (8), and a leading edge reinforcement (32) comprising a fin (32a, 32b) partially covering the aerodynamic surface (28, 30) of the blade (8), characterized in that the fin (32a, 32b) has a radially outer edge (34) arranged in the vicinity of the apex (8d) blade (8) and extending between the leading edge (8a) and the trailing edge (8b), this radially outer edge (34) comprising an upstream point (34a) flush with the apex (8d) of the blade (8) at the leading edge and a point (34b) downstream radially distant from the apex (8d) of the blade (8). Aube (8) selon la revendication 1, dans laquelle la surface aérodynamique est une surface (28) d'extrados, et l'ailette est une ailette (32a) d'extrados.A blade (8) according to claim 1, wherein the aerodynamic surface is an extrados surface (28), and the fin is an extrados fin (32a). Aube (8) selon la revendication 1 ou 2, dans laquelle le bord (34) radialement extérieur de l'ailette (32a, 32b) comprend un point (34c) intermédiaire situé entre le point (34a) amont et le point (34b) aval et définissant avec le point (34a) amont une première portion (36) du bord (34) radialement extérieur , affleurant le sommet (8d) de l'aube (8) et, avec le point (34b) aval, une seconde portion (38) du bord (34) radialement extérieur s'écartant progressivement du sommet (8d) de l'aube (8) en direction du point (34b) aval.A blade (8) according to claim 1 or 2, wherein the radially outer edge (34) of the fin (32a, 32b) comprises an intermediate point (34c) between the upstream point (34a) and the point (34b). downstream and defining with the point (34a) upstream a first portion (36) of the edge (34) radially outer, flush with the apex (8d) of the blade (8) and, with the point (34b) downstream, a second portion (38) radially outer edge (34) progressively diverging from the apex (8d) of the blade (8) towards the point (34b) downstream. Aube (8) selon la revendication 3, dans laquelle le point (34c) intermédiaire est agencé longitudinalement à égale distance du point (34a) amont et du point (34b) aval.A blade (8) according to claim 3, wherein the intermediate point (34c) is arranged longitudinally equidistant from the upstream point (34a) and the downstream point (34b). Aube (8) selon l'une quelconque des revendications 3 à 4, dans laquelle la seconde (38) portion du bord (34) radialement extérieur de l'ailette (32a, 32b) est incurvée convexe.A blade (8) according to any one of claims 3 to 4, wherein the second (38) portion of the radially outer edge (34) of the fin (32a, 32b) is convexly curved. Aube (8) selon l'une des revendications 3 à 5, dans laquelle le point (34c) intermédiaire et le point (34b) aval sont séparés l'un de l'autre d'une distance (H1), mesurée le long d'un axe (M) longitudinal médian de l'ailette, comprise entre 0 et sinα × L ÷ 4
où : - L est la longueur de l'ailette (32a) avant optimisation, c'est-à-dire entre le point (34a) amont et un point (34e) extrême fictif correspondant à la symétrie du point (34a) amont par rapport à l'axe médian (M) sensiblement perpendiculaire à l'axe longitudinal (A) de la turbomachine (2), et passant au moins par le centre du sommet de ladite ailette, et - α est l'angle mesuré entre une ligne passant par le point (34a) amont et le point (34c) intermédiaire du bord (34) radialement extérieur et une tangente (T) au bord (34) radialement extérieur, parallèle à l'axe longitudinal (A) et passant par le point (34c) intermédiaire. Blade (8) according to one of claims 3 to 5, wherein the point (34c) intermediate and the point (34b) downstream are separated from each other by a distance (H1), measured along the a median longitudinal axis (M) of the fin, between 0 and sinα × L ÷ 4
or : - L is the length of the fin (32a) before optimization, that is to say between the point (34a) upstream and a point (34e) fictitious extreme corresponding to the symmetry of the point (34a) upstream with respect to the central axis (M) substantially perpendicular to the longitudinal axis (A) of the turbomachine (2), and passing at least through the center of the top of said fin, and - α is the angle measured between a line passing through the point (34a) upstream and the intermediate point (34c) of the radially outer edge (34) and a tangent (T) at the radially outer edge (34), parallel to the longitudinal axis (A) and passing through the point (34c) intermediate. Aube (8) selon l'une quelconque des revendications précédentes, dans laquelle le renfort (32) de bord d'attaque comprend une ailette (32b) d'intrados recouvrant en partie une surface (30) aérodynamique d'intrados de l'aube (8).A blade (8) according to any one of the preceding claims, wherein the leading edge reinforcement (32) comprises a lower surface fin (32b) partly covering an aerofoil surface (30) of the underside of the dawn (8). Aube (8) selon l'une quelconque des revendications précédentes, dans laquelle le renfort (32) de bord d'attaque est réalisé dans un matériau métallique.A blade (8) according to any one of the preceding claims, wherein the leading edge reinforcement (32) is made of a metallic material. Ensemble (4) comprenant un disque (6) central sur lequel sont montées une pluralité d'aubes (8) selon l'une quelconque des revendications précédentes, lesdites aubes (8) étant régulièrement réparties autour de la périphérie (6a) du disque (6) central, et s'étendant sensiblement radialement par rapport au disque (6) central.Assembly (4) comprising a central disc (6) on which are mounted a plurality of vanes (8) according to any one of the preceding claims, said vanes (8) being evenly distributed around the periphery (6a) of the disc ( 6) and extending substantially radially with respect to the central disk (6). Turbomachine (2) comprenant un ensemble (4) selon la revendication 9.Turbomachine (2) comprising an assembly (4) according to claim 9.
EP17197595.6A 2016-10-28 2017-10-20 Leading-edge reinforcement of a turbine engine blade Active EP3315721B1 (en)

Applications Claiming Priority (1)

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FR1660479A FR3058181B1 (en) 2016-10-28 2016-10-28 REINFORCEMENT OF THE EDGE OF ATTACK OF A TURBOMACHINE BLADE

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FR3085300B1 (en) * 2018-08-31 2022-01-21 Safran Aircraft Engines BLADE IN COMPOSITE MATERIAL WITH REINFORCED ANTI-EROSION FILM AND ASSOCIATED PROTECTION METHOD
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US10746045B2 (en) 2018-10-16 2020-08-18 General Electric Company Frangible gas turbine engine airfoil including a retaining member
FR3103215B1 (en) * 2019-11-20 2021-10-15 Safran Aircraft Engines Turbomachine rotary fan blade, fan and turbomachine fitted therewith
FR3115079B1 (en) * 2020-10-12 2022-10-14 Safran Aircraft Engines BLADE IN COMPOSITE MATERIAL INCLUDING LEADING EDGE SHIELD, TURBOMACHINE INCLUDING BLADE

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CN108005730B (en) 2022-07-08
FR3058181B1 (en) 2018-11-09
EP3315721B1 (en) 2022-03-02
CN108005730A (en) 2018-05-08
US20180119551A1 (en) 2018-05-03
US10316669B2 (en) 2019-06-11

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