[go: up one dir, main page]

EP2438306A1 - Centrifugal impeller for a compressor - Google Patents

Centrifugal impeller for a compressor

Info

Publication number
EP2438306A1
EP2438306A1 EP10734214A EP10734214A EP2438306A1 EP 2438306 A1 EP2438306 A1 EP 2438306A1 EP 10734214 A EP10734214 A EP 10734214A EP 10734214 A EP10734214 A EP 10734214A EP 2438306 A1 EP2438306 A1 EP 2438306A1
Authority
EP
European Patent Office
Prior art keywords
blades
wheel
impeller
trailing edge
blade
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
EP10734214A
Other languages
German (de)
French (fr)
Other versions
EP2438306B1 (en
Inventor
Jérôme PORODO
Nicolas Rochuon
Laurent Tarnowski
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 Helicopter Engines SAS
Original Assignee
Turbomeca SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=41327964&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP2438306(A1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by Turbomeca SA filed Critical Turbomeca SA
Priority to PL10734214T priority Critical patent/PL2438306T3/en
Publication of EP2438306A1 publication Critical patent/EP2438306A1/en
Application granted granted Critical
Publication of EP2438306B1 publication Critical patent/EP2438306B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/30—Vanes
    • 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
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/281—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for fans or blowers
    • F04D29/282—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for fans or blowers the leading edge of each vane being substantially parallel to the rotation axis
    • 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
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • 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
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • F04D29/285—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors the compressor wheel comprising a pair of rotatable bladed hub portions axially aligned and clamped together

Definitions

  • the invention relates to a centrifugal compressor wheel intended to be traversed by a fluid and, in particular, by a gas.
  • This wheel is intended, in particular, to equip a turbomachine compressor.
  • This wheel can equip any type of turbomachine, land or aeronautics, including a helicopter turbine engine.
  • the invention relates to a centrifugal wheel of the type having an axis of rotation, a front portion of small section and a rear portion of large section, the wheel comprising blades each having an upstream edge, or leading edge, and a downstream edge, or trailing edge.
  • the rotation of this impeller draws fluid from the front of the impeller, the axial velocity of the fluid passing through the impeller is progressively transformed into radial velocity, the fluid exiting at the outer periphery of the impeller, at the trailing edge of the blades.
  • Said blades are such that, in a radial cutting plane intersecting the trailing edge of these blades, they are bent in the opposite direction of the rotation of the impeller.
  • upstream and downstream are defined relative to the normal flow direction of the fluid passing through the impeller.
  • the axis of rotation of the impeller is often called more simply "axis of the impeller".
  • the axial direction corresponds to the direction of the axis of the wheel, and a radial direction is a direction perpendicular to this axis and intersecting this axis.
  • an axial plane is a plane containing the axis of the wheel and a radial plane is a plane perpendicular to this axis.
  • the adverbs "axially” and “radially” respectively refer to the axial direction and to a radial direction.
  • the adjectives "inner” and “outer” are used with reference to a radial direction, the inner (ie radially inner) part of an element being closer to the axis of the wheel than the outer part (ie radially outside) of the same element.
  • An aeronautical turbomachine compressor for example a helicopter turbine engine of the centrifugal type or of the mixed axial-centrifugal type comprises one or more compression stages with a centrifugal impeller of the aforementioned type (also called a rotor or centrifugal wheel), an enclosing casing externally the blades of this wheel, and one or more diffusers located downstream of this wheel.
  • a centrifugal impeller of the aforementioned type also called a rotor or centrifugal wheel
  • an enclosing casing externally the blades of this wheel
  • diffusers located downstream of this wheel.
  • Such a compressor is traversed by a fluid which is a gas, usually air.
  • the absolute speed of the gas increases due to the centrifugal acceleration and the pressure of the gas increases due to the diverging section of the channels delimited between the impeller blades.
  • the gas leaves the downstream end of the blades, or trailing edge, at very high speed.
  • a known example of a centrifugal compressor impeller is disclosed in US Patent No. 3973872.
  • the object of the invention is to improve the performance (i.e. total pressure ratio and isentropic efficiency) of a wheel of the aforementioned type, with a corrected flow rate and with a given geometric size.
  • Such a centrifugal compressor wheel may comprise two types of blades: so-called “main” blades and so-called “intermediate” blades.
  • the intermediate blades are interposed between the main blades and are different from the latter in that they are shorter axially; they have a shorter front part, the leading edge of the intermediate blades being set back (ie behind) with respect to the leading edge of the main blades.
  • the wheel comprises only main blades (i.e. no intermediate blades) and these main blades have end fins of the aforementioned type.
  • the impeller comprises main blades and intermediate blades.
  • the main blades are the only ones to present end fins of the aforementioned type, or the intermediate blades are the only ones to present end fins of the aforementioned type, or the main and intermediate blades have end fins of the aforementioned type.
  • said end fin forms with the part of the blade located just upstream of this end fin an obtuse angle greater than or equal to at 155 ° and strictly less than 180 °.
  • this end fin extends from the trailing edge of a main blade of the impeller over a length which, measured along the edge outer (curvilinear) of this main blade, represents less than 15% of the total length of this outer edge and, in particular, more than 2% and less than 10% of the total length of this outer edge.
  • said end fin extends from the trailing edge of the intermediate blade over a length which, measured along the outer edge thereof intermediate blade, represents less than 15% of the total length of this outer edge and, in particular, more than 2% and less than 10% of the total length of this outer edge.
  • the ranges of angle values and fin length above allow, alone or in combination, to further improve the performance of the wheel.
  • the invention also relates to a compressor comprising a centrifugal wheel according to the invention.
  • It may be a centrifugal type compressor, that is to say a compressor having at least one compression stage equipped with a centrifugal impeller, or a compressor of axial-centrifugal mixed type, that is to say a compressor having at least one compression stage equipped with an axial impeller and at least one compression stage equipped with a centrifugal impeller.
  • the invention also relates to a turbomachine and, more particularly, to a helicopter turbine engine comprising a compressor according to the invention.
  • FIG. 1 shows schematically and partially, in axial section, a helicopter turbine engine with a compressor comprising a centrifugal wheel according to the invention (the centrifugal impeller and the turbine engine turbines not being shown in section but in side view) .
  • FIG. 1 schematically shows the centrifugal wheel of Figure 1, isolated from the rest of the turbine engine.
  • FIG. 3 schematically and partially, in perspective, the rear part of two blades of the centrifugal impeller of FIG.
  • FIG. 4 schematically and partially shows the rear portion of one of the blades of FIG. 3, seen in section in a radial section plane intersecting the trailing edge of this blade, this section plane IV-IV being marked in FIG. 2.
  • FIG. 10 The example of a helicopter turbine engine 10 shown in FIG.
  • This compressor 16 comprises a centrifugal wheel 18 according to the invention and a housing 15 surrounding externally the blades 24, 25 of the wheel 18.
  • a diffuser 19 is located downstream of the wheel 18.
  • the turbine engine 10 has an air inlet 12, the air passing through this inlet 12 to reach the compressor 16.
  • the rotation of the wheel 18 about its axis of rotation A draws air from the front of the wheel and the axial velocity of the fluid passing through the wheel 18 is progressively transformed into radial velocity, the fluid exiting the outer periphery of the wheel 18.
  • the air leaving the wheel 18 passes through the diffuser 19 before reaching the combustion chamber 20.
  • the combustion gases leaving the chamber 20 drive a high pressure turbine 22 and a low pressure turbine 23.
  • the wheel 18 is mounted on a shaft 21 which is rotated by the high-pressure turbine 22.
  • the wheel 18 has a front portion of small section and a rear portion of large section.
  • the wheel 18 comprises a plurality of main blades 24 extending axially from the front face 18A of the wheel to a radial flange 17 located at the rear of the wheel 18 and, radially, from the hub of the wheel to the outer periphery of the wheel.
  • Each of the main blades 24 has a leading edge 24A located at the front end of the wheel 18 and a trailing edge 24F located at the outer periphery of the wheel 18, just in front of the radial flange 17.
  • the wheel 18 further comprises intermediate blades 25, interposed between the main blades 24 and which are different from the latter in that they are shorter axially: the leading edge 25A of these blades 25 is set back (ie back) relative to the Leading edge 24A of the main blades 24.
  • the trailing edge 25F of the intermediate blades 25 is at the same radial distance from the axis A as the trailing edge 24F of the blades 24.
  • FIG. 3 shows in detail, in perspective, the rear portion of a main blade 24 and an intermediate blade 25 of the wheel 18.
  • the trailing edge portion of said blades 24, 25, is straightened in the direction of rotation of the impeller so that it forms an end fin 26, 27, to deflect the rotor. flow of air by radially straightening it.
  • FIG. 4 is a sectional view of the main blade 24 in the radial section plane IV-IV of FIG. 2.
  • the main blades 24 and the intermediate blades 25 have end fins 26, 27. In other embodiments, not shown, only the main blades 25 or only the intermediate blades 25 have such blades. end fins.
  • the length (in curvilinear abscissa) of each end fin 26 measured along the curvilinear outer edge 24E of said blade 24 does not represent more than 15% of the total length of this outer edge 24E.
  • the length of the end vane is at least 2% and not more than 10% of the total length of the outer edge 24E.
  • the length (in curvilinear abscissa) of each end fin 27 measured along the curvilinear outer edge 25E of said blade 25 does not represent more than 15% of the total length of this outer edge 25E.
  • the length of the end fin represents at least 2% and not more than 10% of the total length of the outer edge 25E.

Landscapes

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

Abstract

The invention relates to a centrifugal impeller for a compressor, through which a fluid is to pass, said impeller (18) including blades (24, 25), each having a leading edge and a trailing edge (24F, 25F), the rotation of said impeller (18) drawing the fluid at the front of the impeller, said fluid being discharged at the outer periphery of the impeller (18) at the trailing edge (24F, 25F) of the blades, said blades (24, 25) being such that, in a radial cross-section intersecting the trailing edge (24F, 25F) of the blades, the latter are curved in a direction opposite to that of the rotation of the impeller and the trailing edge portion of said blades (24, 25) is straightened in the impeller rotation direction such that it forms an end fin (26, 27) for diverting the fluid flow by radially adjusting same.

Description

Rouet centrifuge de compresseur Centrifugal compressor wheel

L'invention concerne un rouet centrifuge de compresseur destiné à être traversé par un fluide et, notamment, par un gaz. Ce rouet est destiné, en particulier, à équiper un compresseur de turbomachine. Ce rouet peut équiper tout type de turbomachine, terrestre ou aéronautique, et notamment un turbomoteur d'hélicoptère.The invention relates to a centrifugal compressor wheel intended to be traversed by a fluid and, in particular, by a gas. This wheel is intended, in particular, to equip a turbomachine compressor. This wheel can equip any type of turbomachine, land or aeronautics, including a helicopter turbine engine.

Plus particulièrement, l'invention concerne un rouet centrifuge du type présentant un axe de rotation, une partie avant de petite section et une partie arrière de grande section, ce rouet comprenant des pales ayant chacune un bord amont, ou bord d'attaque, et un bord aval, ou bord de fuite. La rotation de ce rouet aspire le fluide par l'avant du rouet, la vitesse axiale du fluide traversant le rouet se transformant progressivement en vitesse radiale, le fluide sortant à la périphérie extérieure du rouet, au niveau du bord de fuite des pales. Lesdites pales sont telles que, dans un plan de coupe radial coupant le bord de fuite de ces pales, elles sont courbées dans le sens inverse de la rotation du rouet. Dans la présente demande, l'amont et l'aval sont définis par rapport au sens d'écoulement normal du fluide traversant le rouet. Par ailleurs, l'axe de rotation du rouet est souvent appelé plus simplement « axe du rouet ». La direction axiale correspond à la direction de l'axe du rouet, et une direction radiale est une direction perpendiculaire à cet axe et coupant cet axe. De même, un plan axial est un plan contenant l'axe du rouet et un plan radial est un plan perpendiculaire à cet axe. Les adverbes « axialement » et « radialement » font respectivement référence à la direction axiale et à une direction radiale.More particularly, the invention relates to a centrifugal wheel of the type having an axis of rotation, a front portion of small section and a rear portion of large section, the wheel comprising blades each having an upstream edge, or leading edge, and a downstream edge, or trailing edge. The rotation of this impeller draws fluid from the front of the impeller, the axial velocity of the fluid passing through the impeller is progressively transformed into radial velocity, the fluid exiting at the outer periphery of the impeller, at the trailing edge of the blades. Said blades are such that, in a radial cutting plane intersecting the trailing edge of these blades, they are bent in the opposite direction of the rotation of the impeller. In the present application, upstream and downstream are defined relative to the normal flow direction of the fluid passing through the impeller. Moreover, the axis of rotation of the impeller is often called more simply "axis of the impeller". The axial direction corresponds to the direction of the axis of the wheel, and a radial direction is a direction perpendicular to this axis and intersecting this axis. Similarly, an axial plane is a plane containing the axis of the wheel and a radial plane is a plane perpendicular to this axis. The adverbs "axially" and "radially" respectively refer to the axial direction and to a radial direction.

Sauf précision contraire, les adjectifs « intérieur » et « extérieur » sont utilisés en référence à une direction radiale, la partie intérieure (i.e. radialement intérieure) d'un élément étant plus proche de l'axe du rouet que la partie extérieure (i.e. radialement extérieure) du même élément.Unless otherwise specified, the adjectives "inner" and "outer" are used with reference to a radial direction, the inner (ie radially inner) part of an element being closer to the axis of the wheel than the outer part (ie radially outside) of the same element.

Enfin, sauf précision contraire, les adjectifs « avant » et « arrière » sont utilisés en référence à la direction axiale, le fluide entrant à l'avant du rouet. Un compresseur de turbomachine aéronautique (par exemple de turbomoteur d'hélicoptère) de type centrifuge ou de type mixte axial- centrifuge comprend un ou plusieurs étage de compression avec un rouet centrifuge du type précité (également appelé rotor ou roue centrifuge), un carter entourant extérieurement les pales de ce rouet, et un ou plusieurs diffuseurs situés en aval de ce rouet. Un tel compresseur est traversé par un fluide qui est un gaz, généralement de l'air.Finally, unless otherwise stated, the adjectives "before" and "back" are used with reference to the axial direction, the fluid entering the front of the wheel. An aeronautical turbomachine compressor (for example a helicopter turbine engine) of the centrifugal type or of the mixed axial-centrifugal type comprises one or more compression stages with a centrifugal impeller of the aforementioned type (also called a rotor or centrifugal wheel), an enclosing casing externally the blades of this wheel, and one or more diffusers located downstream of this wheel. Such a compressor is traversed by a fluid which is a gas, usually air.

Dans le rouet, la vitesse absolue du gaz augmente du fait de l'accélération centrifuge et la pression du gaz augmente du fait de la section divergente des canaux délimités entre les pales du rouet. Ainsi, le gaz quitte l'extrémité avale des pales, ou bord de fuite, à très grande vitesse.In the spinning wheel, the absolute speed of the gas increases due to the centrifugal acceleration and the pressure of the gas increases due to the diverging section of the channels delimited between the impeller blades. Thus, the gas leaves the downstream end of the blades, or trailing edge, at very high speed.

Un exemple connu de rouet centrifuge de compresseur est divulgué dans le brevet US n°3973872. L'invention a pour but d'améliorer les performances (i.e. taux de pression totale et rendement isentropique) d'un rouet du type précité, à débit corrigé et à encombrement géométrique donné.A known example of a centrifugal compressor impeller is disclosed in US Patent No. 3973872. The object of the invention is to improve the performance (i.e. total pressure ratio and isentropic efficiency) of a wheel of the aforementioned type, with a corrected flow rate and with a given geometric size.

Ce but est atteint grâce à un rouet dans lequel, dans ledit plan de coupe radial coupant le bord de fuite des pales du rouet, la partie de bord de fuite de ces pales (i.e. la partie située au niveau de l'extrémité extérieure de la partie arrière des pales) est redressée dans le sens de la rotation du rouet de sorte qu'elle forme une ailette d'extrémité permettant de dévier l'écoulement du fluide en redressant radialement cet écoulement. De manière générale, une telle déviation de l'écoulement du fluide permet d'augmenter le taux de pression totale sans diminuer le rendement isentropique du rouet.This object is achieved by means of a wheel in which, in said radial cutting plane intersecting the trailing edge of the impeller blades, the trailing edge part of these blades (ie the part situated at the outer end of the impeller blade). rear portion of the blades) is straightened in the direction of rotation of the wheel so that it forms an end vane for deflecting the flow of the fluid by radially straightening this flow. In general, such a deviation of the flow of the fluid makes it possible to increase the total pressure ratio without reducing the isentropic efficiency of the impeller.

De plus, en contrôlant au mieux cette déviation, il est possible d'augmenter le taux de pression totale sans produire d'échauffement Ainsi, l'augmentation du taux de pression totale se traduit également par une augmentation plus ou moins importante du rendement isentropique du rouet.Moreover, by optimally controlling this deviation, it is possible to increase the total pressure rate without producing heating. Thus, the increase in the total pressure rate also results in a more or less significant increase in the isentropic efficiency of the pressure. spinning wheel.

Au final, grâce aux ailettes d'extrémité, les performances du rouet sont améliorées. Un tel rouet centrifuge de compresseur peut comprendre deux types de pales : des pales dites « principales » et des pales dites « intermédiaires ». Les pales intermédiaires, optionnelles, sont intercalées entre les pales principales et se différencient de ces dernières en ce qu'elles sont plus courtes axialement ; elles présentent une partie avant plus courte, le bord d'attaque des pales intermédiaires se situant en retrait (i.e. en arrière) par rapport au bord d'attaque des pales principales.In the end, thanks to the end fins, the performance of the wheel is improved. Such a centrifugal compressor wheel may comprise two types of blades: so-called "main" blades and so-called "intermediate" blades. The intermediate blades, optional, are interposed between the main blades and are different from the latter in that they are shorter axially; they have a shorter front part, the leading edge of the intermediate blades being set back (ie behind) with respect to the leading edge of the main blades.

Selon un mode de réalisation, le rouet ne comprend que des pales principales (i.e. pas de pales intermédiaires) et ces pales principales présentent des ailettes d'extrémité du type précité.According to one embodiment, the wheel comprises only main blades (i.e. no intermediate blades) and these main blades have end fins of the aforementioned type.

Selon un autre mode de réalisation, le rouet comprend des pales principales et des pales intermédiaires. Dans ce cas, soit les pales principales sont les seules à présenter des ailettes d'extrémité du type précité, soit les pales intermédiaires sont les seules à présenter des ailettes d'extrémité du type précité, soit les pales principales et les pales intermédiaires présentent des ailettes d'extrémité du type précité.According to another embodiment, the impeller comprises main blades and intermediate blades. In this case, only the main blades are the only ones to present end fins of the aforementioned type, or the intermediate blades are the only ones to present end fins of the aforementioned type, or the main and intermediate blades have end fins of the aforementioned type.

Selon un mode de réalisation, dans ledit plan de coupe radial coupant le bord de fuite des pales du rouet, ladite ailette d'extrémité forme avec la partie de la pale située juste en amont de cette ailette d'extrémité un angle obtus supérieur ou égal à 155° et strictement inférieur à 180°.According to one embodiment, in said radial cutting plane intersecting the trailing edge of the impeller blades, said end fin forms with the part of the blade located just upstream of this end fin an obtuse angle greater than or equal to at 155 ° and strictly less than 180 °.

Selon un mode de réalisation, lorsque les pales principales du rouet présentent une ailette d'extrémité, cette ailette d'extrémité s'étend à partir du bord de fuite d'une pale principale du rouet sur une longueur qui, mesurée le long du bord extérieur (curviligne) de cette pale principale, représente moins de 15 % de la longueur totale de ce bord extérieur et, en particulier, plus de 2% et moins de 10 % de la longueur totale de ce bord extérieur.According to one embodiment, when the main blades of the impeller have an end fin, this end fin extends from the trailing edge of a main blade of the impeller over a length which, measured along the edge outer (curvilinear) of this main blade, represents less than 15% of the total length of this outer edge and, in particular, more than 2% and less than 10% of the total length of this outer edge.

Selon un mode de réalisation, lorsque les pales intermédiaires du rouet présentent une ailette d'extrémité, ladite ailette d'extrémité s'étend à partir du bord de fuite de la pale intermédiaire sur une longueur qui, mesurée le long du bord extérieur de cette pale intermédiaire, représente moins de 15% de la longueur totale de ce bord extérieur et, en particulier, plus de 2% et moins de 10% de la longueur totale de ce bord extérieur. Les plages de valeurs d'angle et de longueur d'ailette précitées permettent, seules ou combinées entre elles, d'améliorer encore les performances du rouet.According to one embodiment, when the intermediate blades of the impeller have an end fin, said end fin extends from the trailing edge of the intermediate blade over a length which, measured along the outer edge thereof intermediate blade, represents less than 15% of the total length of this outer edge and, in particular, more than 2% and less than 10% of the total length of this outer edge. The ranges of angle values and fin length above allow, alone or in combination, to further improve the performance of the wheel.

L'invention concerne également un compresseur comprenant un rouet centrifuge selon l'invention. Il peut s'agir d'un compresseur de type centrifuge, c'est-à-dire un compresseur ayant au moins un étage de compression équipé d'un rouet centrifuge, soit d'un compresseur de type mixte axial-centrifuge, c'est-à-dire un compresseur ayant au moins un étage de compression équipé d'un rouet axial et au moins un étage de compression équipé d'un rouet centrifuge.The invention also relates to a compressor comprising a centrifugal wheel according to the invention. It may be a centrifugal type compressor, that is to say a compressor having at least one compression stage equipped with a centrifugal impeller, or a compressor of axial-centrifugal mixed type, that is to say a compressor having at least one compression stage equipped with an axial impeller and at least one compression stage equipped with a centrifugal impeller.

L'invention concerne également une turbomachine et, plus particulièrement, un turbomoteur d'hélicoptère comprenant un compresseur selon l'invention.The invention also relates to a turbomachine and, more particularly, to a helicopter turbine engine comprising a compressor according to the invention.

L'invention et ses avantages seront encore mieux compris à la lecture de la description détaillée qui suit, d'un exemple de réalisation de l'invention donné à titre illustratif et non limitatif. Cette description fait référence aux figures annexées.The invention and its advantages will be better understood on reading the following detailed description of an exemplary embodiment of the invention given by way of illustration and not limitation. This description refers to the appended figures.

La figure 1 représente schématiquement et partiellement, en coupe axiale, un turbomoteur d'hélicoptère avec un compresseur comprenant un rouet centrifuge selon l'invention (le rouet centrifuge et les turbines du turbomoteur n'étant pas représentés en coupe mais en vue de côté).FIG. 1 shows schematically and partially, in axial section, a helicopter turbine engine with a compressor comprising a centrifugal wheel according to the invention (the centrifugal impeller and the turbine engine turbines not being shown in section but in side view) .

La figure 2 représente schématiquement le rouet centrifuge de la figure 1, isolé du reste du turbomoteur.Figure 2 schematically shows the centrifugal wheel of Figure 1, isolated from the rest of the turbine engine.

La figure 3 représente schématiquement et partiellement, en perspective, la partie arrière de deux pales du rouet centrifuge de la figure 1.FIG. 3 schematically and partially, in perspective, the rear part of two blades of the centrifugal impeller of FIG.

La figure 4 représente schématiquement et partiellement la partie arrière d'une des pales de la figure 3, vue en coupe dans un plan de coupe radial coupant le bord de fuite de cette pale, ce plan de coupe IV-IV étant repéré sur la figure 2.FIG. 4 schematically and partially shows the rear portion of one of the blades of FIG. 3, seen in section in a radial section plane intersecting the trailing edge of this blade, this section plane IV-IV being marked in FIG. 2.

L'exemple de turbomoteur 10 d'hélicoptère représenté sur la figureThe example of a helicopter turbine engine 10 shown in FIG.

1 comprend un compresseur 16 de type centrifuge à un seul étage de compression. Ce compresseur 16 comprend un rouet centrifuge 18 selon l'invention et un carter 15 entourant extérieurement les pales 24, 25 du rouet 18. Un diffuseur 19 est situé en aval du rouet 18. Le turbomoteur 10 présente une entrée d'air 12, l'air passant par cette entrée 12 pour atteindre le compresseur 16. La rotation du rouet 18 autour de son axe de rotation A, aspire l'air par l'avant du rouet et la vitesse axiale du fluide qui traverse le rouet 18 se transforme progressivement en vitesse radiale, le fluide sortant à la périphérie extérieure du rouet 18. L'air pénètre dans le rouet 18 suivant une direction plutôt parallèle à l'axe A de rotation du rouet, représentée sur la coupe de la figure 1 par les flèches Fl, et sort du rouet 18 suivant une direction plutôt perpendiculaire à l'axe A, représentée par les flèches F2. L'air sortant du rouet 18 traverse le diffuseur 19 avant d'atteindre la chambre de combustion 20. Les gaz de combustion sortant de la chambre 20 entraînent une turbine haute pression 22 et une turbine basse pression 23.1 comprises a compressor 16 of the centrifugal type with a single compression stage. This compressor 16 comprises a centrifugal wheel 18 according to the invention and a housing 15 surrounding externally the blades 24, 25 of the wheel 18. A diffuser 19 is located downstream of the wheel 18. The turbine engine 10 has an air inlet 12, the air passing through this inlet 12 to reach the compressor 16. The rotation of the wheel 18 about its axis of rotation A, draws air from the front of the wheel and the axial velocity of the fluid passing through the wheel 18 is progressively transformed into radial velocity, the fluid exiting the outer periphery of the wheel 18. The air enters the wheel 18 in a direction rather parallel to the axis A of rotation of the wheel, shown on the section of Figure 1 by the arrows Fl, and out of the wheel 18 in a direction rather perpendicular to the axis A, represented by the arrows F2. The air leaving the wheel 18 passes through the diffuser 19 before reaching the combustion chamber 20. The combustion gases leaving the chamber 20 drive a high pressure turbine 22 and a low pressure turbine 23.

Le rouet 18 est monté sur un arbre 21 qui est entraîné en rotation par la turbine haute pression 22.The wheel 18 is mounted on a shaft 21 which is rotated by the high-pressure turbine 22.

En référence à la figure 2, le rouet 18 présente une partie avant de petite section et une partie arrière de grande section. Le rouet 18 comporte une pluralité de pales principales 24 s'étendant, axialement, depuis la face avant 18A du rouet jusqu'à un flasque radial 17 situé à l'arrière du rouet 18 et, radialement, depuis le moyeu du rouet jusqu'à la périphérie extérieure du rouet. Chacune des pales principales 24 présente un bord d'attaque 24A situé à l'extrémité avant du rouet 18 et un bord de fuite 24F situé à la périphérie extérieure du rouet 18, juste en avant du flasque radial 17. Le rouet 18 comporte en outre des pales intermédiaires 25, intercalées entre les pales principales 24 et qui se différencient de ces dernières en ce qu'elles sont plus courtes axialement : le bord d'attaque 25A de ces pales 25 se situe en retrait (i.e. en arrière) par rapport au bord d'attaque 24A des pales principales 24. En revanche, le bord de fuite 25F des pales intermédiaires 25 se situe à la même distance radiale de l'axe A que le bord de fuite 24F des pales 24.Referring to Figure 2, the wheel 18 has a front portion of small section and a rear portion of large section. The wheel 18 comprises a plurality of main blades 24 extending axially from the front face 18A of the wheel to a radial flange 17 located at the rear of the wheel 18 and, radially, from the hub of the wheel to the outer periphery of the wheel. Each of the main blades 24 has a leading edge 24A located at the front end of the wheel 18 and a trailing edge 24F located at the outer periphery of the wheel 18, just in front of the radial flange 17. The wheel 18 further comprises intermediate blades 25, interposed between the main blades 24 and which are different from the latter in that they are shorter axially: the leading edge 25A of these blades 25 is set back (ie back) relative to the Leading edge 24A of the main blades 24. On the other hand, the trailing edge 25F of the intermediate blades 25 is at the same radial distance from the axis A as the trailing edge 24F of the blades 24.

La figure 3 représente en détail, en perspective, la partie arrière d'une pale principale 24 et d'une pale intermédiaire 25 du rouet 18.FIG. 3 shows in detail, in perspective, the rear portion of a main blade 24 and an intermediate blade 25 of the wheel 18.

Dans un plan de coupe radial (i.e. perpendiculaire à l'axe A) coupant le bord de fuite 24F, 25F des pales 24, 25, du rouet 18, comme le plan IV-IV de la figure 2, les pales 24, 25, sont courbées dans le sens inverse de Ia rotation du rouet, Ie sens de rotation du rouet 18 étant symbolisé par la flèche R sur les figures 3 et 4.In a radial sectional plane (ie perpendicular to the axis A) intersecting the trailing edge 24F, 25F of the blades 24, 25, of the impeller 18, like the plane IV-IV of FIG. 2, the blades 24, 25, are bent in the direction inverse of the rotation of the wheel, the direction of rotation of the wheel 18 being symbolized by the arrow R in FIGS. 3 and 4.

Dans ce même plan de coupe radial, la partie de bord de fuite desdites pales 24, 25, est redressée dans le sens de la rotation du rouet de sorte qu'elle forme une ailette d'extrémité 26, 27, permettant de dévier l'écoulement de l'air en redressant radialement celui-ci.In this same radial sectional plane, the trailing edge portion of said blades 24, 25, is straightened in the direction of rotation of the impeller so that it forms an end fin 26, 27, to deflect the rotor. flow of air by radially straightening it.

Dans ce plan de coupe radial, l'ailette d'extrémité 26, 27, forme avec la partie de la pale 24, 25, située juste en amont de cette ailette 26, 27, un angle obtus T supérieur ou égal à 155° et strictement inférieur à 180°. Cet angle T est repéré sur la figure 4 qui est une vue en coupe de la pale principale 24 dans le plan de coupe radial IV-IV de la figure 2.In this radial sectional plane, the end fin 26, 27 forms with the part of the blade 24, 25, situated just upstream of this fin 26, 27, an obtuse angle T greater than or equal to 155 ° and strictly less than 180 °. This angle T is marked in FIG. 4 which is a sectional view of the main blade 24 in the radial section plane IV-IV of FIG. 2.

Dans l'exemple représenté, les pales principales 24 et les pales intermédiaires 25 présentent des ailettes d'extrémité 26, 27. Dans d'autres exemples de réalisation, non représentés, seules les pales principales 25 ou seules les pales intermédiaires 25 présentent de telles ailettes d'extrémité.In the example shown, the main blades 24 and the intermediate blades 25 have end fins 26, 27. In other embodiments, not shown, only the main blades 25 or only the intermediate blades 25 have such blades. end fins.

Selon un exemple de réalisation, lorsque les ailettes d'extrémité 26 sont présentes sur les pales principales 24, la longueur (en abscisse curviligne) de chaque ailette d'extrémité 26 mesurée le long du bord extérieur curviligne 24E de ladite pale 24 ne représente pas plus de 15 % de la longueur totale de ce bord extérieur 24E. Par exemple, la longueur de l'ailette d'extrémité représente au moins 2% et pas plus de 10 % de la longueur totale du bord extérieur 24E.According to an exemplary embodiment, when the end fins 26 are present on the main blades 24, the length (in curvilinear abscissa) of each end fin 26 measured along the curvilinear outer edge 24E of said blade 24 does not represent more than 15% of the total length of this outer edge 24E. For example, the length of the end vane is at least 2% and not more than 10% of the total length of the outer edge 24E.

Selon un exemple de réalisation, lorsque les ailettes d'extrémité 27 sont présentes sur les pales intermédiaires 25, la longueur (en abscisse curviligne) de chaque ailette d'extrémité 27 mesurée le long du bord extérieur curviligne 25E de ladite pale 25 ne représente pas plus de 15% de la longueur totale de ce bord extérieur 25E. En particulier, la longueur de l'ailette d'extrémité représente au moins 2% et pas plus de 10% de la longueur totale du bord extérieur 25E. According to an exemplary embodiment, when the end fins 27 are present on the intermediate blades 25, the length (in curvilinear abscissa) of each end fin 27 measured along the curvilinear outer edge 25E of said blade 25 does not represent more than 15% of the total length of this outer edge 25E. In particular, the length of the end fin represents at least 2% and not more than 10% of the total length of the outer edge 25E.

Claims

REVENDICATIONS 1. Rouet centrifuge de compresseur destiné à être traversé par un fluide, ce rouet (18) présentant un axe de rotation (A), une partie avant de petite section et une partie arrière de grande section, ce rouet (18) comprenant des pales (24, 25) ayant chacune un bord d'attaque (24A, 25A) et un bord de fuite (24F, 25F), la rotation de ce rouet (18) aspirant le fluide par l'avant du rouet, la vitesse axiale du fluide traversant le rouet se transformant progressivement en vitesse radiale, ce fluide sortant à la périphérie extérieure du rouet (18), au niveau du bord de fuite (24F, 25F) des pales, ces pales (24, 25) étant telles que, dans un plan de coupe radial coupant le bord de fuite (24F, 25F) de ces pales, elles sont courbées dans le sens inverse de la rotation du rouet, ce rouet (18) étant caractérisé en ce que, dans ledit plan de coupe radial, la partie de bord de fuite desdites pales (24, 25) est redressée dans le sens de la rotation du rouet de sorte qu'elle forme une ailette d'extrémité (26, 27) permettant de dévier l'écoulement du fluide en redressant radialement celui-ci, et en ce que ladite ailette d'extrémité (26, 27) s'étend à partir du bord de fuite (24F, 25F) de la pale sur une longueur qui, mesurée le long du bord extérieur (24E, 25E) de cette pale (24, 25), représente moins de 15% de la longueur totale de ce bord extérieur (24E, 25E).1. Centrifugal compressor wheel intended to be traversed by a fluid, the wheel (18) having an axis of rotation (A), a small section front portion and a large section rear portion, the wheel (18) comprising blades (24, 25) each having a leading edge (24A, 25A) and a trailing edge (24F, 25F), the rotation of the impeller (18) drawing the fluid from the front of the impeller, the axial speed of the fluid passing through the wheel progressively transforming into radial velocity, this fluid exiting at the outer periphery of the impeller (18), at the trailing edge (24F, 25F) of the blades, these blades (24, 25) being such that, in a radial cutting plane intersecting the trailing edge (24F, 25F) of these blades, they are curved in the opposite direction to the rotation of the wheel, this wheel (18) being characterized in that, in said radial section plane, the trailing edge portion of said blades (24, 25) is straightened in the direction of rotation of the impeller so that it forms a end fin (26, 27) for deflecting fluid flow by radially straightening thereof, and said end fin (26, 27) extends from the trailing edge (24F, 25F) of the blade along a length which, measured along the outer edge (24E, 25E) of this blade (24, 25), is less than 15% of the total length of this outer edge (24E, 25E). 2. Rouet centrifuge de compresseur selon la revendication 1, dans lequel, dans ledit plan de coupe radial, ladite ailette d'extrémité (26, 27) forme avec la partie de la pale située juste en amont de cette ailette d'extrémité un angle (T) obtus supérieur ou égal à 155° et strictement inférieur à 180°.The centrifugal compressor wheel according to claim 1, wherein, in said radial section plane, said end fin (26, 27) forms with the portion of the blade just upstream of said end fin an angle (T) obtuse greater than or equal to 155 ° and strictly less than 180 °. 3. Rouet centrifuge de compresseur selon la revendication 1 ou 2, comprenant des pales principales (24) et, éventuellement, des pales intermédiaires (25) situées entre les pales principales et plus courtes axialement que les pales principales, dans lequel lesdites pales principales (24) et/ou lesdïtes pales intermédiaires (25) présentent lesdites ailettes d'extrémité (26, 27). Centrifugal compressor wheel according to claim 1 or 2, comprising main blades (24) and, optionally, intermediate blades (25) located between the main blades and shorter axially than the main blades, in which said main blades ( 24) and / or the intermediate blade tips (25) have said end fins (26, 27). 4. Rouet centrifuge de compresseur selon la revendication 3, dans lequel les pales principales (24) présentent lesdites ailettes d'extrémité (26).Centrifugal compressor wheel according to claim 3, wherein the main blades (24) have said end fins (26). 5. Rouet centrifuge de compresseur selon la revendication 4, dans lequel ladite ailette d'extrémité (26) s'étend à partir du bord de fuite (24F) d'une pale principale (24) sur une longueur qui, mesurée le long du bord extérieur (24E) de cette pale principale (24), représentant plus de 2% et moins de 10 % de la longueur totale de ce bord extérieur (24E).The centrifugal compressor wheel according to claim 4, wherein said end fin (26) extends from the trailing edge (24F) of a main blade (24) to a length which, measured along the outer edge (24E) of this main blade (24), representing more than 2% and less than 10% of the total length of this outer edge (24E). 6. Rouet centrifuge de compresseur selon l'une quelconque des revendications 3 à 5, dans lequel les pales intermédiaires (25) présentent lesdites ailettes d'extrémité (27).Centrifugal compressor wheel according to any one of claims 3 to 5, wherein the intermediate blades (25) have said end fins (27). 7. Rouet centrifuge de compresseur selon la revendication 6, dans lequel, le long du bord extérieur (25E) d'une pale intermédiaire (25), ladite ailette d'extrémité (27) s'étend à partir du bord de fuite (25F) de la pale intermédiaire (25) sur une longueur qui, mesurée le long du bord extérieur (25E) de cette pale intermédiaire, représente plus de 2% et moins de 10% de la longueur totale de ce bord extérieur (25E).A compressor centrifugal wheel according to claim 6, wherein, along the outer edge (25E) of an intermediate blade (25), said end fin (27) extends from the trailing edge (25F). ) of the intermediate blade (25) over a length which, measured along the outer edge (25E) of this intermediate blade, represents more than 2% and less than 10% of the total length of this outer edge (25E). 8. Compresseur comprenant un rouet centrifuge (18) selon l'une quelconque des revendications 1 à 7.8. Compressor comprising a centrifugal wheel (18) according to any one of claims 1 to 7. 9. Turbomachine comprenant un compresseur selon la revendication 8. 9. A turbomachine comprising a compressor according to claim 8.
EP10734214.9A 2009-06-05 2010-06-02 Centrifugal impeller of compressor Active EP2438306B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL10734214T PL2438306T3 (en) 2009-06-05 2010-06-02 Centrifugal impeller of compressor

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0953757A FR2946399B1 (en) 2009-06-05 2009-06-05 CENTRIFUGAL COMPRESSOR WHEEL.
PCT/FR2010/051078 WO2010139901A1 (en) 2009-06-05 2010-06-02 Centrifugal impeller for a compressor

Publications (2)

Publication Number Publication Date
EP2438306A1 true EP2438306A1 (en) 2012-04-11
EP2438306B1 EP2438306B1 (en) 2019-07-31

Family

ID=41327964

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10734214.9A Active EP2438306B1 (en) 2009-06-05 2010-06-02 Centrifugal impeller of compressor

Country Status (10)

Country Link
US (1) US20120087800A1 (en)
EP (1) EP2438306B1 (en)
JP (1) JP5705839B2 (en)
KR (1) KR101750121B1 (en)
CN (1) CN102459916B (en)
CA (1) CA2762308A1 (en)
FR (1) FR2946399B1 (en)
PL (1) PL2438306T3 (en)
RU (1) RU2525365C2 (en)
WO (1) WO2010139901A1 (en)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP5722367B2 (en) * 2013-02-28 2015-05-20 テラル株式会社 Centrifugal blower
CN103527510A (en) * 2013-09-16 2014-01-22 苏州格园机械有限公司 Fan structure of mowing machine
JP2017193985A (en) * 2016-04-19 2017-10-26 本田技研工業株式会社 Turbine impeller
CN107989823B (en) * 2017-12-26 2023-12-01 北京伯肯节能科技股份有限公司 Impeller, centrifugal compressor and fuel cell system
JP6740271B2 (en) * 2018-03-05 2020-08-12 三菱重工業株式会社 Impeller and centrifugal compressor equipped with this impeller
FR3089576B1 (en) 2018-12-05 2022-11-25 Safran Helicopter Engines Centrifugal impeller
CN110566500B (en) * 2019-10-12 2024-08-16 浙江科贸智能机电股份有限公司 Impeller of centrifugal ventilator

Family Cites Families (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3973872A (en) * 1975-08-01 1976-08-10 Konstantin Pavlovich Seleznev Centrifugal compressor
JPS55134797A (en) * 1979-04-06 1980-10-20 Hitachi Ltd Centrifugal vane
DE3275000D1 (en) * 1981-08-07 1987-02-12 Holset Engineering Co Impeller for centrifugal compressor
SU1231273A1 (en) * 1984-11-23 1986-05-15 Всесоюзный Научно-Исследовательский И Проектно-Конструкторский Институт Атомного И Энергетического Насосостроения Impeller of centrifugal pump
EP0205001A1 (en) * 1985-05-24 1986-12-17 A. S. Kongsberg Väpenfabrikk Splitter blade arrangement for centrifugal compressors
DE19516515A1 (en) * 1995-05-05 1996-11-07 Sel Alcatel Ag Radial fan
JPH1037893A (en) * 1996-07-26 1998-02-13 Japan Servo Co Ltd Centrifugal fan
US5951245A (en) * 1997-10-06 1999-09-14 Ford Motor Company Centrifugal fan assembly for an automotive vehicle
JPH11280695A (en) * 1998-03-26 1999-10-15 Kubota Corp Centrifugal blower for fertilizer application equipment
GB2337795A (en) * 1998-05-27 1999-12-01 Ebara Corp An impeller with splitter blades
JP2000145693A (en) * 1998-11-09 2000-05-26 Hitachi Ltd Multi-wing forward fan
JP2001012389A (en) * 1999-06-28 2001-01-16 Atago Seisakusho:Kk Impeller of multiblade fan
JP2001082383A (en) * 1999-09-09 2001-03-27 Sowa Denki Seisakusho:Kk Impeller, centrifugal blower, and centrifugal pump
JP2002332993A (en) * 2001-05-09 2002-11-22 Toyota Central Res & Dev Lab Inc Centrifugal compressor impeller
RU24253U1 (en) * 2001-10-31 2002-07-27 Акционерное общество "Техника-Технология-Конструкции" WATER RING COMPRESSOR ROTOR
RU22978U1 (en) * 2001-11-13 2002-05-10 Караджи Вячеслав Георгиевич RADIAL FAN OPERATING WHEEL
JP2005069183A (en) * 2003-08-27 2005-03-17 Japan Servo Co Ltd Impeller of centrifugal fan
GB0403869D0 (en) * 2004-02-21 2004-03-24 Holset Engineering Co Compressor
JP4670285B2 (en) * 2004-09-02 2011-04-13 パナソニック株式会社 Impeller and blower fan having the same
JP2007192034A (en) 2006-01-17 2007-08-02 Matsushita Electric Ind Co Ltd Electric blower and electric vacuum cleaner using the same
JP2007247594A (en) * 2006-03-17 2007-09-27 Teral Kyokuto Inc Centrifugal blower including backward impeller
DE102007017822A1 (en) * 2007-04-16 2008-10-23 Continental Automotive Gmbh turbocharger
US8007241B2 (en) * 2007-11-27 2011-08-30 Nidec Motor Corporation Bi-directional cooling fan

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2010139901A1 *

Also Published As

Publication number Publication date
JP2012528979A (en) 2012-11-15
JP5705839B2 (en) 2015-04-22
EP2438306B1 (en) 2019-07-31
PL2438306T3 (en) 2019-12-31
RU2525365C2 (en) 2014-08-10
CA2762308A1 (en) 2010-12-09
CN102459916A (en) 2012-05-16
FR2946399B1 (en) 2016-05-13
WO2010139901A1 (en) 2010-12-09
CN102459916B (en) 2015-04-29
RU2011153687A (en) 2013-07-20
KR20120034670A (en) 2012-04-12
US20120087800A1 (en) 2012-04-12
KR101750121B1 (en) 2017-06-22
FR2946399A1 (en) 2010-12-10

Similar Documents

Publication Publication Date Title
EP2438306B1 (en) Centrifugal impeller of compressor
EP2809883B1 (en) Jet engine fan blade
FR3130897A1 (en) AIRCRAFT TURBOMACHINE
CA2794825C (en) Method for adapting the air flow of a turbine engine having a centrifugal compressor and diffuser for implementing same
EP2085620B1 (en) Jet engine compressor
CA2880146A1 (en) Turbomachine comprising a plurality of fixed radial blades mounted upstream of the fan
WO2014154997A1 (en) Radial or mixed-flow compressor diffuser having vanes
EP1574685A1 (en) Turbojet having two counterrotating fans integral with a counterrotating low pressure compressor
EP2582986B1 (en) Aerodynamic coupling between two annular rows of stationary vanes in a turbine engine
EP2917590B1 (en) Compression assembly for a turbine engine
FR2970508A1 (en) Bi-centrifugal compressor assembly for turbine engine of helicopter, has compression stage, and diffuser joint that is coupled to compressor stage of centrifugal compressor via air return channel that is inclined upstream
FR3089576A1 (en) Centrifugal impeller
EP4100625B1 (en) Rotor blade for a turbomachine
EP4508311A1 (en) Stator part having a fin, in a turbine engine
WO2019214915A1 (en) Turbine-engine including an air collection circuit
EP4508310A1 (en) Stator part having a fin, in a turbine engine
BE1028097B1 (en) Turbomachine compressor blade, compressor and turbomachine fitted therewith
FR3121170A1 (en) TURBOMACHINE TURBINE IMPELLER BLADE
FR3027354B1 (en) AUBES WHEEL COMPRISING DRILLING BETWEEN THE INTRADOS AND THE EXTRADOS OF THE DAWN AND ASSOCIATED MOTOR
EP4584477A1 (en) Guide vane for attachment to a stator shroud of a gas turbine engine, gas turbine engine stator assembly and gas turbine engine
FR3162062A1 (en) Tandem system of stator blades comprising an upstream blade with variable pitch and a downstream blade with fixed pitch
WO2025056842A1 (en) Turbine engine blade assembly
FR3009348B1 (en) DIFFUSER FOR A RADIAL OR MIXED COMPRESSOR OF AN ENGINE COMPRISING A FLASK OF WHICH A PART IS MOBILE
FR3126143A1 (en) Intermediate housing hub incorporating a secondary flow deflector
FR3088687A1 (en) ASSEMBLY FOR A TURBOMACHINE COMPRESSOR

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: 20111202

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 SE SI SK SM TR

RIN1 Information on inventor provided before grant (corrected)

Inventor name: TARNOWSKI, LAURENT

Inventor name: PORODO, JEROME

Inventor name: ROCHUON, NICOLAS

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

Owner name: SAFRAN HELICOPTER ENGINES

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: 20190327

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

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

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

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

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1161196

Country of ref document: AT

Kind code of ref document: T

Effective date: 20190815

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: 602010060278

Country of ref document: DE

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20190731

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1161196

Country of ref document: AT

Kind code of ref document: T

Effective date: 20190731

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

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: 20190731

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: 20190731

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: 20190731

Ref country code: SE

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: 20190731

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: 20191031

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: 20191202

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: 20190731

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: 20190731

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: 20191031

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

Ref country code: ES

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

Effective date: 20190731

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: 20191101

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: 20191130

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: 20190731

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: 20190731

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: 20190731

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

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: 20190731

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: 20190731

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: 20190731

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

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: 20190731

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: 20190731

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: 20200224

REG Reference to a national code

Ref country code: DE

Ref legal event code: R026

Ref document number: 602010060278

Country of ref document: DE

PLBI Opposition filed

Free format text: ORIGINAL CODE: 0009260

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

Free format text: ORIGINAL CODE: EPIDOSNOBS2

26 Opposition filed

Opponent name: RAYTHEON TECHNOLOGIES CORPORATION

Effective date: 20200602

PG2D Information on lapse in contracting state deleted

Ref country code: IS

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

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: 20191030

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: 20190731

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

Free format text: ORIGINAL CODE: EPIDOSNOBS3

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

Ref country code: 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: 20190731

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: LU

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

Effective date: 20200602

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20200630

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: 20200602

Ref country code: LI

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

Effective date: 20200630

Ref country code: CH

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

Effective date: 20200630

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: 20200630

REG Reference to a national code

Ref country code: DE

Ref legal event code: R100

Ref document number: 602010060278

Country of ref document: DE

PLCK Communication despatched that opposition was rejected

Free format text: ORIGINAL CODE: EPIDOSNREJ1

PLBN Opposition rejected

Free format text: ORIGINAL CODE: 0009273

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

Free format text: STATUS: OPPOSITION REJECTED

27O Opposition rejected

Effective date: 20211118

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: 20190731

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: 20190731

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: 20190731

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

Ref country code: CZ

Payment date: 20230526

Year of fee payment: 14

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

Ref country code: PL

Payment date: 20230525

Year of fee payment: 14

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

Ref country code: CZ

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

Effective date: 20240602

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

Ref country code: CZ

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

Effective date: 20240602

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

Ref country code: DE

Payment date: 20250618

Year of fee payment: 16

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

Ref country code: GB

Payment date: 20250625

Year of fee payment: 16

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

Ref country code: FR

Payment date: 20250623

Year of fee payment: 16

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 NON-PAYMENT OF DUE FEES

Effective date: 20240602

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

Ref country code: IT

Payment date: 20250630

Year of fee payment: 16