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EP2766577B1 - Turbomachine compressor blade comprising a curved portion - Google Patents

Turbomachine compressor blade comprising a curved portion Download PDF

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Publication number
EP2766577B1
EP2766577B1 EP12780239.5A EP12780239A EP2766577B1 EP 2766577 B1 EP2766577 B1 EP 2766577B1 EP 12780239 A EP12780239 A EP 12780239A EP 2766577 B1 EP2766577 B1 EP 2766577B1
Authority
EP
European Patent Office
Prior art keywords
blade
turbomachine
curved
curved portion
radial
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP12780239.5A
Other languages
German (de)
French (fr)
Other versions
EP2766577A1 (en
Inventor
Damien CELLIER
Alicia Lise Julia DUFRESNE
Philippe Pierre Marcel Marie PELLETRAU
Vincent Paul Gabriel Perrot
Jean-François Antoine Christian RIOS
Laurent Christophe Francis VILLAINES
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 EP2766577A1 publication Critical patent/EP2766577A1/en
Application granted granted Critical
Publication of EP2766577B1 publication Critical patent/EP2766577B1/en
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Classifications

    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • 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
    • F01D5/16—Form or construction for counteracting blade vibration
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using 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
    • F04D29/321—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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/403—Casings; Connections of working fluid especially adapted for elastic fluid pumps
    • 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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise

Definitions

  • the invention relates to a turbomachine blade which is made to limit the coincidences of vibration frequencies of the blade with respect to the urging frequencies of the blade during operation of the turbomachine, which could lead to deterioration of dawn or his breakage.
  • stator vanes During the operation of a turbomachine, the flow of gas along the stator vanes causes the vanes to vibrate.
  • Each blade has one or more eigenfrequencies for which the amplitude of the vibration can become too important and cause the deterioration or breakage of the dawn.
  • This curvature makes it possible to limit the vibrations of the blade in a frequency range corresponding to the operating conditions of the turbomachine, and also limits the risks of breakage of the blade.
  • the documents EP 1 462 608 A1 and WO 2011/124214 A2 also describe curved vanes.
  • the aim of the invention is to propose a turbomachine blade which is made in such a way that the at least one eigenfrequency of the blade is different from the biasing frequencies of the blade during operation of the turbomachine.
  • the invention proposes a turbomachine compressor blade according to claim 1.
  • the curved portion tangentially modifies the vibration response of the blade to vibrational stresses, and distances the so-called risk frequencies out of the operating range of the blade. .
  • the radial length L1 of the curved portion is between 30% and 60% of the radial length L of the blade.
  • the tangential amplitude A of the curved portion is between 1% and 5% of the radial length L of the blade.
  • said rectilinear portion is inclined at an angle less than or equal to 30 ° with respect to the radial main direction of the blade.
  • the domed portion is positioned radially at the foot portion.
  • the domed portion is positioned radially at the head portion.
  • the domed portion is positioned radially at the middle portion.
  • the curved portion is convex tangentially towards the underside of the blade.
  • the invention also proposes a turbomachine compressor stator comprising radial vanes distributed around the main axis of the turbomachine, characterized in that each blade is produced as defined above.
  • the invention also proposes a turbomachine comprising a stator which comprises blades as defined above.
  • the radial, tangential and axial orientations according to the reference R, T, A indicated in FIG. figure 1 in which the radial orientation is the main orientation of the blade and the tangential orientation is the orientation perpendicular to a main axial plane of the blade.
  • figure 1 a blade 10 forming part of a stator (not shown) of the compressor of a turbomachine.
  • the compressor comprises a plurality of blades 10 which are regularly distributed around the main axis of the turbomachine, to form an annular assembly, called a stator grid, which is traversed by a flow of gas, here air .
  • the blade 10 extends radially generally along the orientation R with respect to the main axis of the turbomachine.
  • the blade 10 has a radially inner portion 12, called the root of the blade, at which the blade 10 is attached to an inner shell of the compressor (not shown).
  • the blade 10 has a radially outer portion 14 called the head of the blade, at which the blade 10 is fixed to an outer shell of the compressor (not shown).
  • the blade 10 has an intermediate portion 16 connecting the foot 12 to the head 14 of the blade 10.
  • the inner ferrule and the outer ferrule of the compressor delimit an annular duct called a vein, in which the flow of air circulates and interacts with the blade 10.
  • the blade 10 also comprises a leading edge 18, which is located axially upstream in the direction of gas flow with respect to the blade 10, and a trailing edge 20 which is located axially downstream along the direction. gas flow with respect to the blade 10.
  • the blade 10 is further arched and has a face 22 called intrados, which is located on the side opposite the camber and a face 24 called extrados which is located on the side of the arch.
  • This tangential stacking law corresponds to the position of the center of gravity of each section of the blade in a plane perpendicular to the radial main direction of the blade, with respect to a radial main axis of the blade 10.
  • This curve 26 has a foot portion 28 corresponding to the foot 12 of the blade 10, a head portion 30 corresponding to the head 14 of the blade 10 and an intermediate portion 32 corresponding to the intermediate portion 16 of the blade 10 .
  • the blade 10 is made in such a way that it comprises a part 34 which is curved tangentially and at least a rectilinear part.
  • the curve 26 has a curved portion tangentially 36 corresponding to the convex portion 34.
  • the curve 26 also comprises at least one rectilinear portion corresponding to the straight portion of the blade 10.
  • the rectilinear portion of the blade 10 is situated at the level of the foot 12 and / or at the level of the head 14 of the blade 10, depending on the position of the curved portion 34.
  • the rectilinear portion of the curve 26 is situated at the level of the foot portion 28 and / or at the level of the head portion 30, as a function of the radial position of the convex portion 36.
  • the convex portion 34 is located radially at the level of the foot 12 of the blade 10.
  • the rectilinear portion is then located at the head 14 of the blade 10. Consequently, the portion curved 36 is located radially at the foot portion 28 and the leading portion 30 of the curve 26 is rectilinear.
  • the convex portion 34 is located radially at the head 14 of the blade 10.
  • the rectilinear portion is then located at the level of the root 12 of the blade 10.
  • the curved portion 36 of the curve 26 is therefore located radially at the level of the head portion 30 and the foot portion 28 of the curve 26 is rectilinear.
  • the convex portion 34 is located radially at the intermediate portion 16 of the blade 10.
  • the foot 12 and the head 14 of the blade 10 each form a straight portion of the blade 10.
  • the convex portion 36 is located radially at the intermediate portion 32 and the foot portion 28 and the leading portion 30 of the curve 26 are both straight.
  • the blade 10 is curved in such a manner that the convex portion 34 is convex tangentially in the direction of the intrados 22, as shown in FIG. figure 1 .
  • the convex portion 34 is curved toward the extrados 24.
  • the dimensions of the convex portion 36 are defined with respect to the radial length "L" of the blade 10.
  • the radial dimension "L1" of the convex portion 36 is between 30% and 60% of the radial dimension "L" of the blade 10.
  • the tangential dimension "A" of the convex portion 36 is between 1% and 5% of the radial dimension "L" of the blade 10.
  • the foot portion 28 and / or the head portion 30 is rectilinear.
  • each portion of head 28 and / or foot 30 which is rectilinear, is inclined relative to the radial main direction of the blade by an angle whose value is less than or equal to 30 °.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

DOMAINE TECHNIQUETECHNICAL AREA

L'invention concerne une aube de turbomachine qui est réalisée de manière à limiter les coïncidences de fréquences de vibration de l'aube par rapport aux fréquences de sollicitation de l'aube lors du fonctionnement de la turbomachine, qui risqueraient d'aboutir à une détérioration de l'aube ou bien sa casse.The invention relates to a turbomachine blade which is made to limit the coincidences of vibration frequencies of the blade with respect to the urging frequencies of the blade during operation of the turbomachine, which could lead to deterioration of dawn or his breakage.

ÉTAT DE LA TECHNIQUE ANTÉRIEURESTATE OF THE PRIOR ART

Lors du fonctionnement d'une turbomachine, l'écoulement de gaz le long des aubes de stator provoquent la mise en vibration des aubes.During the operation of a turbomachine, the flow of gas along the stator vanes causes the vanes to vibrate.

Chaque aube possède une ou plusieurs fréquences propres pour lesquelles l'amplitude de la vibration peut devenir trop importante et provoquer la détérioration ou la casse de l'aube.Each blade has one or more eigenfrequencies for which the amplitude of the vibration can become too important and cause the deterioration or breakage of the dawn.

Le document US 3.745.629 décrit une aube de turbomachine qui est courbée selon un profil qui est similaire au profil d'une aube en vibration dans une de ses fréquences propres.The document US 3,745,629 describes a turbomachine blade which is curved in a profile which is similar to the profile of a blade in vibration in one of its own frequencies.

Cette courbure permet de limiter les vibrations de l'aube dans une plage de fréquences correspondant aux conditions de fonctionnement de la turbomachine, et limite aussi les risques de casse de l'aube.This curvature makes it possible to limit the vibrations of the blade in a frequency range corresponding to the operating conditions of the turbomachine, and also limits the risks of breakage of the blade.

Cependant, une telle courbure réduit aussi l'efficacité et le rendement aérodynamique de l'aube.However, such a curvature also reduces the efficiency and aerodynamic efficiency of the blade.

Les documents EP 1 462 608 A1 et WO 2011/124214 A2 décrivent aussi des aubes courbeés. L'invention a pour but de proposer une aube de turbomachine qui est réalisée de manière que la ou les fréquences propres de l'aube sont différentes des fréquences de sollicitation de l'aube lors du fonctionnement de la turbomachine.The documents EP 1 462 608 A1 and WO 2011/124214 A2 also describe curved vanes. The aim of the invention is to propose a turbomachine blade which is made in such a way that the at least one eigenfrequency of the blade is different from the biasing frequencies of the blade during operation of the turbomachine.

EXPOSÉ DE L'INVENTIONSTATEMENT OF THE INVENTION

L'invention propose une aube de compresseur de turbomachine selon la revendication 1. La portion bombée tangentiellement modifie la réponse en vibration de l'aube aux sollicitations en vibration, et éloigne les fréquences dites à risque hors de la plage de fonctionnement de l'aube.The invention proposes a turbomachine compressor blade according to claim 1. The curved portion tangentially modifies the vibration response of the blade to vibrational stresses, and distances the so-called risk frequencies out of the operating range of the blade. .

De préférence, la longueur radiale L1 de la partie bombée est comprise entre 30% et 60% de la longueur radiale L de l'aube.Preferably, the radial length L1 of the curved portion is between 30% and 60% of the radial length L of the blade.

L'amplitude tangentielle A de la partie bombée est comprise entre 1% et 5% de la longueur radiale L de l'aube.The tangential amplitude A of the curved portion is between 1% and 5% of the radial length L of the blade.

De préférence, la dite partie rectiligne est inclinée d'un angle inférieur ou égal à 30° par rapport à la direction principale radiale de l'aube.Preferably, said rectilinear portion is inclined at an angle less than or equal to 30 ° with respect to the radial main direction of the blade.

De préférence, la partie bombée est positionnée radialement au niveau de la partie de pied.Preferably, the domed portion is positioned radially at the foot portion.

De préférence, la partie bombée est positionnée radialement au niveau de la partie de tête.Preferably, the domed portion is positioned radially at the head portion.

De préférence, la partie bombée est positionnée radialement au niveau de la partie médiane.Preferably, the domed portion is positioned radially at the middle portion.

De préférence, la partie bombée est bombée tangentiellement en direction de l'intrados de l'aube.Preferably, the curved portion is convex tangentially towards the underside of the blade.

L'invention propose aussi un stator de compresseur de turbomachine comportant des aubes radiales réparties autour de l'axe principal de la turbomachine, caractérisé en ce que chaque aube est réalisée tel que défini précédemment.The invention also proposes a turbomachine compressor stator comprising radial vanes distributed around the main axis of the turbomachine, characterized in that each blade is produced as defined above.

L'invention propose aussi une turbomachine comportant un stator qui comporte des aubes telles que définies précédemment.The invention also proposes a turbomachine comprising a stator which comprises blades as defined above.

BRÈVE DESCRIPTION DES DESSINSBRIEF DESCRIPTION OF THE DRAWINGS

D'autres caractéristiques et avantages de l'invention apparaîtront à la lecture de la description détaillée qui suit pour la compréhension de laquelle on se reportera aux figures annexées parmi lesquelles :

  • la figure 1 est une représentation schématique en perspective d'une aube comportant une portion bombée selon l'invention ;
  • la figure 2 est une représentation de la loi d'empilage tangentiel du centre de gravité des sections d'une aube selon l'invention.
Other characteristics and advantages of the invention will appear on reading the detailed description which follows for the understanding of which reference will be made to the appended figures among which:
  • the figure 1 is a schematic representation in perspective of a blade having a convex portion according to the invention;
  • the figure 2 is a representation of the tangential stacking law of the center of gravity of the sections of a blade according to the invention.

EXPOSÉ DÉTAILLÉ DE MODES DE RÉALISATION PARTICULIERSDETAILED PRESENTATION OF PARTICULAR EMBODIMENTS

Dans la description qui va suivre, des éléments identiques, similaires ou analogues seront désignés par les mêmes chiffres de référence.In the following description, identical, similar or similar elements will be designated by the same reference numerals.

Pour la description de l'invention, on adoptera à titre non limitatif les orientations radiale, tangentielle et axiale selon le repère R, T, A indiqué à la figure 1, dans lequel l'orientation radiale est l'orientation principale de l'aube et l'orientation tangentielle est l'orientation perpendiculaire à un plan axial principal de l'aube.For the description of the invention, the radial, tangential and axial orientations according to the reference R, T, A indicated in FIG. figure 1 in which the radial orientation is the main orientation of the blade and the tangential orientation is the orientation perpendicular to a main axial plane of the blade.

On a représenté à la figure 1 une aube 10 faisant partie d'un stator (non représenté) du compresseur d'une turbomachine.We have shown figure 1 a blade 10 forming part of a stator (not shown) of the compressor of a turbomachine.

Le compresseur comporte une pluralité d'aubes 10 qui sont réparties de manière régulière autour de l'axe principal de la turbomachine, pour former un ensemble annulaire, appelé grille de redresseur, qui est traversé par un flux de gaz, ici de l'air.The compressor comprises a plurality of blades 10 which are regularly distributed around the main axis of the turbomachine, to form an annular assembly, called a stator grid, which is traversed by a flow of gas, here air .

L'aube 10 s'étend globalement radialement selon l'orientation R par rapport à l'axe principal de la turbomachine.The blade 10 extends radially generally along the orientation R with respect to the main axis of the turbomachine.

L'aube 10 comporte une partie radialement interne 12, appelée pied de l'aube, au niveau de laquelle l'aube 10 est fixée à une virole interne du compresseur (non représentée).The blade 10 has a radially inner portion 12, called the root of the blade, at which the blade 10 is attached to an inner shell of the compressor (not shown).

L'aube 10 comporte une partie radialement externe 14 appelée tête de l'aube, au niveau de laquelle l'aube 10 est fixée à une virole externe du compresseur (non représentée).The blade 10 has a radially outer portion 14 called the head of the blade, at which the blade 10 is fixed to an outer shell of the compressor (not shown).

L'aube 10 comporte une partie intermédiaire 16 reliant le pied 12 à la tête 14 de l'aube 10.The blade 10 has an intermediate portion 16 connecting the foot 12 to the head 14 of the blade 10.

La virole interne et la virole externe du compresseur délimitent un conduit annulaire appelé veine, dans lequel le flux d'air circule et interagit avec l'aube 10.The inner ferrule and the outer ferrule of the compressor delimit an annular duct called a vein, in which the flow of air circulates and interacts with the blade 10.

L'aube 10 comporte aussi un bord d'attaque 18, qui est situé axialement en amont selon le sens d'écoulement de gaz par rapport à l'aube 10, et un bord de fuite 20 qui est situé axialement en aval selon le sens d'écoulement de gaz par rapport à l'aube 10.The blade 10 also comprises a leading edge 18, which is located axially upstream in the direction of gas flow with respect to the blade 10, and a trailing edge 20 which is located axially downstream along the direction. gas flow with respect to the blade 10.

L'aube 10 est en outre cambrée et comporte une face 22 appelée intrados, qui est située du côté opposé à la cambrure et une face 24 appelée extrados qui est située du côté de la cambrure.The blade 10 is further arched and has a face 22 called intrados, which is located on the side opposite the camber and a face 24 called extrados which is located on the side of the arch.

On a représenté à la figure 2 une courbe 26 représentant la loi d'empilage tangentiel du centre de gravité des sections de l'aube 10.We have shown figure 2 a curve 26 representing the tangential stacking law of the center of gravity of the sections of the blade 10.

Cette loi d'empilage tangentiel correspond à la position du centre de gravité de chaque section de l'aube selon un plan perpendiculaire à la direction principale radiale de l'aube, par rapport à un axe principal radial de l'aube 10.This tangential stacking law corresponds to the position of the center of gravity of each section of the blade in a plane perpendicular to the radial main direction of the blade, with respect to a radial main axis of the blade 10.

Cette courbe 26 comporte une portion de pied 28 correspondant au pied 12 de l'aube 10, une portion de tête 30 correspondant à la tête 14 de l'aube 10 et une portion intermédiaire 32 correspondant à la partie intermédiaire 16 de l'aube 10.This curve 26 has a foot portion 28 corresponding to the foot 12 of the blade 10, a head portion 30 corresponding to the head 14 of the blade 10 and an intermediate portion 32 corresponding to the intermediate portion 16 of the blade 10 .

Selon l'invention, l'aube 10 est réalisée de manière qu'elle comporte une partie 34 qui est bombée tangentiellement et au moins une partie rectiligne.According to the invention, the blade 10 is made in such a way that it comprises a part 34 which is curved tangentially and at least a rectilinear part.

Ainsi, comme on peut le voir plus en détails à la figure 2, la courbe 26 comporte une portion bombée tangentiellement 36 correspondant à la partie bombée 34. La courbe 26 comporte aussi au moins une portion rectiligne correspondant à la partie rectiligne de l'aube 10.So, as we can see more in detail at the figure 2 , the curve 26 has a curved portion tangentially 36 corresponding to the convex portion 34. The curve 26 also comprises at least one rectilinear portion corresponding to the straight portion of the blade 10.

Selon l'invention, la partie rectiligne de l'aube 10 est située au niveau du pied 12 et/ou au niveau de la tête 14 de l'aube 10, selon la position de la partie bombée 34.According to the invention, the rectilinear portion of the blade 10 is situated at the level of the foot 12 and / or at the level of the head 14 of the blade 10, depending on the position of the curved portion 34.

Ainsi, la portion rectiligne de la courbe 26 est située au niveau de la portion de pied 28 et/ou au niveau de la portion de tête 30, en fonction de la position radiale de la portion bombée 36.Thus, the rectilinear portion of the curve 26 is situated at the level of the foot portion 28 and / or at the level of the head portion 30, as a function of the radial position of the convex portion 36.

Selon un premier aspect de l'invention, la partie bombée 34 est située radialement au niveau du pied 12 de l'aube 10. La partie rectiligne est alors située au niveau de la tête 14 de l'aube 10. Par conséquent, la portion bombée 36 est située radialement au niveau de la portion de pied 28 et la portion de tête 30 de la courbe 26 est rectiligne.According to a first aspect of the invention, the convex portion 34 is located radially at the level of the foot 12 of the blade 10. The rectilinear portion is then located at the head 14 of the blade 10. Consequently, the portion curved 36 is located radially at the foot portion 28 and the leading portion 30 of the curve 26 is rectilinear.

Selon un deuxième aspect de l'invention, la partie bombée 34 est située radialement au niveau de la tête 14 de l'aube 10. La partie rectiligne est alors située au niveau du pied 12 de l'aube 10. La portion bombée 36 de la courbe 26 est par conséquent située radialement au niveau de la portion de tête 30 et la portion de pied 28 de la courbe 26 est rectiligne.According to a second aspect of the invention, the convex portion 34 is located radially at the head 14 of the blade 10. The rectilinear portion is then located at the level of the root 12 of the blade 10. The curved portion 36 of the curve 26 is therefore located radially at the level of the head portion 30 and the foot portion 28 of the curve 26 is rectilinear.

Selon un troisième aspect de l'invention, la partie bombée 34 est située radialement au niveau de la partie intermédiaire 16 de l'aube 10. Le pied 12 et la tête 14 de l'aube 10 forment chacun une partie rectiligne de l'aube 10.According to a third aspect of the invention, the convex portion 34 is located radially at the intermediate portion 16 of the blade 10. The foot 12 and the head 14 of the blade 10 each form a straight portion of the blade 10.

Par conséquent, la portion bombée 36 est située radialement au niveau de la portion intermédiaire 32 et la portion de pied 28 et la portion de tête 30 de la courbe 26 sont toutes les deux rectilignes.Therefore, the convex portion 36 is located radially at the intermediate portion 32 and the foot portion 28 and the leading portion 30 of the curve 26 are both straight.

En outre, selon un mode de réalisation préféré, l'aube 10 est bombée de manière telle que la partie bombée 34 est bombée tangentiellement en direction de l'intrados 22, comme représenté à la figure 1.In addition, according to a preferred embodiment, the blade 10 is curved in such a manner that the convex portion 34 is convex tangentially in the direction of the intrados 22, as shown in FIG. figure 1 .

Selon une variante de réalisation non représentée, la partie bombée 34 est bombée en direction de l'extrados 24.According to an alternative embodiment not shown, the convex portion 34 is curved toward the extrados 24.

Les dimensions de la portion bombée 36 sont définies par rapport à la longueur radiale "L" de l'aube 10.The dimensions of the convex portion 36 are defined with respect to the radial length "L" of the blade 10.

Ainsi, la dimension radiale "L1" de la portion bombée 36 est comprise entre 30% et 60% de la dimension radiale "L" de l'aube 10.Thus, the radial dimension "L1" of the convex portion 36 is between 30% and 60% of the radial dimension "L" of the blade 10.

Aussi, la dimension tangentielle "A" de la portion bombée 36 est comprise entre 1% et 5 % de la dimension radiale "L" de l'aube 10.Also, the tangential dimension "A" of the convex portion 36 is between 1% and 5% of the radial dimension "L" of the blade 10.

Comme on l'a dit précédemment, selon la position radiale de la portion bombée, la portion de pied 28 et/ou la portion de tête 30 est rectiligne.As previously mentioned, depending on the radial position of the curved portion, the foot portion 28 and / or the head portion 30 is rectilinear.

Dans ce cas, chaque portion de tête 28 et/ou de pied 30 qui est rectiligne, est inclinée par rapport à la direction principale radiale de l'aube d'un angle dont la valeur est inférieure ou égale à 30°.In this case, each portion of head 28 and / or foot 30 which is rectilinear, is inclined relative to the radial main direction of the blade by an angle whose value is less than or equal to 30 °.

Claims (9)

  1. Turbomachine compressor blade (10) of main radial orientation with respect to the main axis of the turbomachine,
    the blade (10) comprising a radially internal root portion (12), a radially external tip portion (14) and a radially intermediate portion (16),
    wherein the blade (10), comprises a curved portion (34) curved perpendicularly to a main axial plane of the blade in a direction and at least one straight portion on the root portion (12) and/or on the tip portion (14),
    characterised in that the tangential amplitude A of the curved portion (34) is between 1% and 5% of the radial length L of the blade (10).
  2. Blade (10) as claimed in the preceding claim, characterised in that the radial length L1 of the curved portion (34) is between 30% and 60% of the radial length L of the blade (10).
  3. Blade (10) as claimed in any preceding claim, characterised in that said straight portion is inclined by an angle less than or equal to 30° with respect to the main radial direction of the blade (10).
  4. Blade (10) as claimed in any preceding claim characterised in that the curved portion (34) is positioned radially on the root portion (12).
  5. Blade (10) according to any of claims 1 to 3, characterised in that the curved portion (34) is positioned radially on the tip portion (14).
  6. Blade (10) according to any of claims 1 to 3, characterised in that the curved portion (34) is positioned radially on the median portion (16).
  7. Blade (10) as claimed in any preceding claim, characterised in that the curved portion (34) is tangentially curved in the direction of the intrados of the blade (10).
  8. Turbomachine compressor stator comprising radial blades (10) distributed around the main axis of the turbomachine,
    characterised in that each blade (10) is carried out as claimed in any preceding claim.
  9. Turbomachine comprising a stator that comprises blades (10) as claimed in the preceding claim.
EP12780239.5A 2011-10-13 2012-10-11 Turbomachine compressor blade comprising a curved portion Active EP2766577B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1159255A FR2981396A1 (en) 2011-10-13 2011-10-13 TURBOMACHINE STATOR VANE COMPRISING A BOMBED PORTION
PCT/FR2012/052314 WO2013054049A1 (en) 2011-10-13 2012-10-11 Turbomachine centre blade comprising a curved portion

Publications (2)

Publication Number Publication Date
EP2766577A1 EP2766577A1 (en) 2014-08-20
EP2766577B1 true EP2766577B1 (en) 2018-12-05

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP12780239.5A Active EP2766577B1 (en) 2011-10-13 2012-10-11 Turbomachine compressor blade comprising a curved portion

Country Status (9)

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US (1) US10309419B2 (en)
EP (1) EP2766577B1 (en)
JP (1) JP2014528552A (en)
CN (1) CN103857880B (en)
BR (1) BR112014008623B1 (en)
CA (1) CA2850901C (en)
FR (1) FR2981396A1 (en)
RU (1) RU2641768C2 (en)
WO (1) WO2013054049A1 (en)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3003598B1 (en) 2013-03-20 2018-04-06 Safran Aircraft Engines DAWN AND ANGEL OF DIEDRE D'AUBE
FR3010462B1 (en) 2013-09-11 2021-10-08 Snecma ANGULAR SECTOR OF RECTIFIER FOR TURBOMACHINE COMPRESSOR WITH A BRUSH SEAL
US9938854B2 (en) * 2014-05-22 2018-04-10 United Technologies Corporation Gas turbine engine airfoil curvature
FR3043428B1 (en) * 2015-11-10 2020-05-29 Safran Aircraft Engines TURBOMACHINE RECTIFIER DAWN
US10760587B2 (en) 2017-06-06 2020-09-01 Elliott Company Extended sculpted twisted return channel vane arrangement
CN107829985B (en) * 2017-09-28 2019-09-10 中国航发动力股份有限公司 A kind of modification method of aeroengine fan blades intrinsic frequency
JP7260845B2 (en) * 2019-01-16 2023-04-19 株式会社Ihi turbine rotor blade

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3745629A (en) * 1972-04-12 1973-07-17 Secr Defence Method of determining optimal shapes for stator blades
SU1613701A1 (en) * 1988-07-15 1990-12-15 Харьковский авиационный институт им.Н.Е.Жуковского Blade of axial-flow turbomachine
JPH06212902A (en) 1993-01-20 1994-08-02 Toshiba Corp Turbine moving blade
JP3697296B2 (en) * 1995-08-25 2005-09-21 株式会社東芝 Turbine blade
FR2853022B1 (en) * 2003-03-27 2006-07-28 Snecma Moteurs DOUBLE CURVED RECTIFIER DRAW
CN200949477Y (en) * 2006-08-25 2007-09-19 哈尔滨汽轮机厂有限责任公司 Large-scale full speed nuclear steam turbine last stage blade
US7806653B2 (en) 2006-12-22 2010-10-05 General Electric Company Gas turbine engines including multi-curve stator vanes and methods of assembling the same
US7794201B2 (en) 2006-12-22 2010-09-14 General Electric Company Gas turbine engines including lean stator vanes and methods of assembling the same
DE102008055824B4 (en) * 2007-11-09 2016-08-11 Alstom Technology Ltd. steam turbine
RU2381388C1 (en) * 2008-07-07 2010-02-10 Открытое акционерное общество "Научно-производственное объединение "Сатурн" Fan or compressor impeller
US8167567B2 (en) 2008-12-17 2012-05-01 United Technologies Corporation Gas turbine engine airfoil
JP4923073B2 (en) 2009-02-25 2012-04-25 株式会社日立製作所 Transonic wing
DE102010014556B4 (en) * 2010-04-10 2013-01-03 Mtu Aero Engines Gmbh Guide vane of a compressor

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
JP2014528552A (en) 2014-10-27
EP2766577A1 (en) 2014-08-20
CA2850901A1 (en) 2013-04-18
BR112014008623B1 (en) 2021-11-09
BR112014008623A2 (en) 2017-04-18
FR2981396A1 (en) 2013-04-19
US10309419B2 (en) 2019-06-04
WO2013054049A1 (en) 2013-04-18
RU2014118768A (en) 2015-11-20
CN103857880A (en) 2014-06-11
CA2850901C (en) 2019-10-29
US20140248144A1 (en) 2014-09-04
CN103857880B (en) 2016-07-13
RU2641768C2 (en) 2018-01-22

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