EP2766577B1 - Aube de stator de turbomachine comportant une portion bombée - Google Patents

Aube de stator de turbomachine comportant une portion bombée Download PDF

Info

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)
English (en)
Other versions
EP2766577A1 (fr
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/fr
Application granted granted Critical
Publication of EP2766577B1 publication Critical patent/EP2766577B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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 °.

Landscapes

  • 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 TECHNIQUE
  • 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.
    • ÉTAT DE LA TECHNIQUE ANTÉRIEURE
  • Lors du fonctionnement d'une turbomachine, l'écoulement de gaz le long des aubes de stator provoquent la mise en vibration des aubes.
  • 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.
  • 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.
  • 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.
  • Cependant, une telle courbure réduit aussi l'efficacité et le rendement aérodynamique de l'aube.
  • 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.
    • EXPOSÉ DE L'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.
  • De préférence, la longueur radiale L1 de la partie bombée est comprise entre 30% et 60% de la longueur radiale L de l'aube.
  • L'amplitude tangentielle A de la partie bombée est comprise entre 1% et 5% de la longueur radiale L de l'aube.
  • 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.
  • De préférence, la partie bombée est positionnée radialement au niveau de la partie de pied.
  • De préférence, la partie bombée est positionnée radialement au niveau de la partie de tête.
  • De préférence, la partie bombée est positionnée radialement au niveau de la partie médiane.
  • De préférence, la partie bombée est bombée tangentiellement en direction de l'intrados de l'aube.
  • 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.
  • L'invention propose aussi une turbomachine comportant un stator qui comporte des aubes telles que définies précédemment.
    • BRÈVE DESCRIPTION DES DESSINS
  • 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.
    EXPOSÉ DÉTAILLÉ DE MODES DE RÉALISATION PARTICULIERS
  • Dans la description qui va suivre, des éléments identiques, similaires ou analogues seront désignés par les mêmes chiffres de référence.
  • 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.
  • On a représenté à la figure 1 une aube 10 faisant partie d'un stator (non représenté) du compresseur d'une 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.
  • L'aube 10 s'étend globalement radialement selon l'orientation R par rapport à l'axe principal de la 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).
  • 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).
  • L'aube 10 comporte une partie intermédiaire 16 reliant le pied 12 à la tête 14 de l'aube 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • Selon une variante de réalisation non représentée, la partie bombée 34 est bombée en direction de l'extrados 24.
  • Les dimensions de la portion bombée 36 sont définies par rapport à la longueur radiale "L" de l'aube 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.
  • 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.
  • 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.
  • 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°.

Claims (9)

  1. Aube (10) de compresseur de turbomachine d'orientation principale radiale par rapport à l'axe principal de la turbomachine,
    l'aube (10) comportant une partie radialement interne de pied (12), une partie radialement externe de tête (14) et une partie radialement intermédiaire (16),
    dans laquelle l'aube (10), comporte une partie bombée (34) perpendiculairement à un plan axial principal de l'aube dans une direction et au moins une partie rectiligne au niveau de la partie de pied (12) et/ou au niveau de la partie de tête (14),
    caractérisée en ce que l'amplitude tangentielle A de la partie bombée (34) est comprise entre 1% et 5% de la longueur radiale L de l'aube (10).
  2. Aube (10) selon la revendication précédente, caractérisée en ce que la longueur radiale L1 de la partie bombée (34) est comprise entre 30% et 60% de la longueur radiale L de l'aube (10).
  3. Aube (10) selon l'une quelconque des revendications précédentes, caractérisée en ce que la dite partie rectiligne est inclinée d'un angle inférieur ou égal à 30° par rapport à la direction principale radiale de l'aube (10).
  4. Aube (10) selon l'une quelconque des revendications précédentes caractérisée en ce que la partie bombée (34) est positionnée radialement au niveau de la partie de pied (12).
  5. Aube (10) selon l'une quelconque des revendications 1 à 3, caractérisée en ce que la partie bombée (34) est positionnée radialement au niveau de la partie de tête (14).
  6. Aube (10) selon l'une quelconque des revendications 1 à 3, caractérisée en ce que la partie bombée (34) est positionnée radialement au niveau de la partie médiane (16).
  7. Aube (10) selon l'une quelconque des revendications précédentes, caractérisée en ce que la partie bombée (34) est bombée tangentiellement en direction de l'intrados de l'aube (10).
  8. Stator de compresseur de turbomachine comportant des aubes (10) radiales réparties autour de l'axe principal de la turbomachine,
    caractérisé en ce que chaque aube (10) est réalisée selon l'une quelconque des revendications précédentes.
  9. Turbomachine comportant un stator qui comporte des aubes (10) selon la revendication précédente.
EP12780239.5A 2011-10-13 2012-10-11 Aube de stator de turbomachine comportant une portion bombée Active EP2766577B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1159255A FR2981396A1 (fr) 2011-10-13 2011-10-13 Aube de stator de turbomachine comportant une portion bombee
PCT/FR2012/052314 WO2013054049A1 (fr) 2011-10-13 2012-10-11 Aube de stator de turbomachine comportant une portion bombée

Publications (2)

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

Family

ID=47116069

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12780239.5A Active EP2766577B1 (fr) 2011-10-13 2012-10-11 Aube de stator de turbomachine comportant une portion bombée

Country Status (9)

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

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3003598B1 (fr) 2013-03-20 2018-04-06 Safran Aircraft Engines Aube et angle de diedre d'aube
FR3010462B1 (fr) 2013-09-11 2021-10-08 Snecma Secteur angulaire de redresseur pour compresseur de turbomachine comportant un joint d'etancheite a brosse
US9938854B2 (en) 2014-05-22 2018-04-10 United Technologies Corporation Gas turbine engine airfoil curvature
FR3043428B1 (fr) * 2015-11-10 2020-05-29 Safran Aircraft Engines Aube de redresseur de turbomachine
US10760587B2 (en) 2017-06-06 2020-09-01 Elliott Company Extended sculpted twisted return channel vane arrangement
CN107829985B (zh) * 2017-09-28 2019-09-10 中国航发动力股份有限公司 一种航空发动机风扇叶片固有频率的修正方法
JP7260845B2 (ja) * 2019-01-16 2023-04-19 株式会社Ihi タービン動翼

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 (ru) * 1988-07-15 1990-12-15 Харьковский авиационный институт им.Н.Е.Жуковского Лопатка осевой турбомашины
JPH06212902A (ja) 1993-01-20 1994-08-02 Toshiba Corp タービン動翼
JP3697296B2 (ja) * 1995-08-25 2005-09-21 株式会社東芝 タービン動翼
FR2853022B1 (fr) * 2003-03-27 2006-07-28 Snecma Moteurs Aube de redresseur a double courbure
CN200949477Y (zh) 2006-08-25 2007-09-19 哈尔滨汽轮机厂有限责任公司 一种大型全转速核电汽轮机末级叶片
US7794201B2 (en) 2006-12-22 2010-09-14 General Electric Company Gas turbine engines including lean stator vanes and methods of assembling the same
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
DE102008055824B4 (de) 2007-11-09 2016-08-11 Alstom Technology Ltd. Dampfturbine
RU2381388C1 (ru) * 2008-07-07 2010-02-10 Открытое акционерное общество "Научно-производственное объединение "Сатурн" Рабочая лопата вентилятора или компрессора
US8167567B2 (en) 2008-12-17 2012-05-01 United Technologies Corporation Gas turbine engine airfoil
JP4923073B2 (ja) * 2009-02-25 2012-04-25 株式会社日立製作所 遷音速翼
DE102010014556B4 (de) * 2010-04-10 2013-01-03 Mtu Aero Engines Gmbh Leitschaufel eines Verdichters

Non-Patent Citations (1)

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

Also Published As

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

Similar Documents

Publication Publication Date Title
EP2766577B1 (fr) Aube de stator de turbomachine comportant une portion bombée
EP2483565B1 (fr) Rotor d'un compresseur de turbomachine a paroi d'extremite interne optimisee
CA2862280C (fr) Aube pour soufflante de turboreacteur
EP2901021B2 (fr) Carter et roue a aubes de turbomachine
CA2647057C (fr) Distributeur sectorise pour une turbomachine
CA2873942A1 (fr) Aube de soufflante pour turboreacteur d'avion a profil cambre en sections de pied
FR3058181A1 (fr) Renfort de bord d'attaque d'une aube de turbomachine
FR3081185A1 (fr) Element de stator de turbomachine
EP2795068B1 (fr) Redresseur de compresseur pour turbomachine
JP2002047944A (ja) 高回転型インペラ
FR3043428A1 (fr) Aube de redresseur de turbomachine
EP3473813B1 (fr) Turbomachine comprenant un ensemble de redressement
CA3168255A1 (fr) Rotor a pales integrees
EP3607211B1 (fr) Diffuseur axial renforcé
JP4946901B2 (ja) インペラ構造
EP2872782B1 (fr) Aube de turbomachine ayant un profil configuré de manière à obtenir des propriétés aérodynamiques et mécaniques améliorées
FR3065497B1 (fr) Canal d'ejection d'air vers le sommet et vers l'aval d'une pale d'aube de turbomachine
WO2020021192A1 (fr) Aube de turbine
BE1030039B1 (fr) Separateur de flux dans une turbomachine
FR2933150A1 (fr) Etage redresseur dans un compresseur de turbomachine
BE1028234B1 (fr) Aube pour compresseur de turbomachine
BE1030472B1 (fr) Separateur de flux dans une turbomachine triple-flux
WO2023021258A1 (fr) Pièce statorique d'une turbomachine comprenant une pale et une ailette définissant entre elles une surface décroissante d'amont en aval selon le sens d'écoulement des gaz
FR3144634A1 (fr) aubage amélioré pour compresseur de turbomachine.

Legal Events

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

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20140422

AK Designated contracting states

Kind code of ref document: A1

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

DAX Request for extension of the european patent (deleted)
GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20180508

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SAFRAN AIRCRAFT ENGINES

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

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

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

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

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1073323

Country of ref document: AT

Kind code of ref document: T

Effective date: 20181215

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: FRENCH

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602012054392

Country of ref document: DE

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20181205

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1073323

Country of ref document: AT

Kind code of ref document: T

Effective date: 20181205

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

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

Ref country code: AT

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

Effective date: 20181205

Ref country code: LV

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

Effective date: 20181205

Ref country code: HR

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

Effective date: 20181205

Ref country code: FI

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

Effective date: 20181205

Ref country code: BG

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

Effective date: 20190305

Ref country code: ES

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

Effective date: 20181205

Ref country code: LT

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

Effective date: 20181205

Ref country code: NO

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

Effective date: 20190305

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

Ref country code: GR

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

Effective date: 20190306

Ref country code: RS

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

Effective date: 20181205

Ref country code: AL

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

Effective date: 20181205

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

Ref country code: NL

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

Effective date: 20181205

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

Ref country code: PL

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

Effective date: 20181205

Ref country code: PT

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

Effective date: 20190405

Ref country code: CZ

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

Effective date: 20181205

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

Ref country code: SK

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

Effective date: 20181205

Ref country code: SM

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

Effective date: 20181205

Ref country code: EE

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

Effective date: 20181205

Ref country code: IS

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

Effective date: 20190405

Ref country code: RO

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

Effective date: 20181205

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602012054392

Country of ref document: DE

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

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

Ref country code: SI

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

Effective date: 20181205

Ref country code: DK

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

Effective date: 20181205

26N No opposition filed

Effective date: 20190906

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

Ref country code: TR

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

Effective date: 20181205

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

Ref country code: MC

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

Effective date: 20181205

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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

Ref country code: CH

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

Effective date: 20191031

Ref country code: LI

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

Effective date: 20191031

Ref country code: LU

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

Effective date: 20191011

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20191031

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

Ref country code: BE

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

Effective date: 20191031

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

Ref country code: IE

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

Effective date: 20191011

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

Ref country code: CY

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

Effective date: 20181205

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

Ref country code: MT

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

Effective date: 20181205

Ref country code: HU

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

Effective date: 20121011

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

Ref country code: MK

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

Effective date: 20181205

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

Ref country code: IT

Payment date: 20230920

Year of fee payment: 12

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

Ref country code: SE

Payment date: 20230922

Year of fee payment: 12

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

Ref country code: DE

Payment date: 20230920

Year of fee payment: 12

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

Ref country code: GB

Payment date: 20240919

Year of fee payment: 13

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

Ref country code: FR

Payment date: 20240919

Year of fee payment: 13