EP2978977B1 - Vane for radial or mixed-flow compressor - Google Patents

Vane for radial or mixed-flow compressor Download PDF

Info

Publication number
EP2978977B1
EP2978977B1 EP14718669.6A EP14718669A EP2978977B1 EP 2978977 B1 EP2978977 B1 EP 2978977B1 EP 14718669 A EP14718669 A EP 14718669A EP 2978977 B1 EP2978977 B1 EP 2978977B1
Authority
EP
European Patent Office
Prior art keywords
leading edge
vane
trailing edge
radial
diffuser
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
EP14718669.6A
Other languages
German (de)
French (fr)
Other versions
EP2978977A1 (en
Inventor
Laurent Tarnowski
Nicolas BULOT
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
Application filed by Turbomeca SA filed Critical Turbomeca SA
Publication of EP2978977A1 publication Critical patent/EP2978977A1/en
Application granted granted Critical
Publication of EP2978977B1 publication Critical patent/EP2978977B1/en
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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F04D29/444—Bladed diffusers
    • 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
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • F04D17/12—Multi-stage pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/52—Outlet

Definitions

  • the invention relates generally to gas turbine engines, and more particularly to a fin of a diffuser for a radial or mixed compressor, a diffusion stage of a radial or mixed compressor of a gas turbine, and 'to an associated compressor.
  • a compressor comprises one or more rotating disks (rotor or wheel), bladed or not and one or more fixed vane wheels (rectifier stages).
  • a radial (or centrifugal) compressor has at least one radial compression stage, that is to say capable of producing a flow of gas perpendicular to the central axis of the compressor. It comprises at least one radial impeller which sucks the air axially, which, under the effect of the radial force, is accelerated, compressed and discharged radially. This air is then straightened in a diffuser (fixed blade) which transforms part of its speed into static pressure by slowing the gases at the exit of the wheel. The operation must take place with a minimum of total pressure loss while maintaining a satisfactory compressor stability level in order to maintain an acceptable pumping margin for the operation of the turbomachine.
  • the gases are then guided to the combustion chamber.
  • a mixed compressor (or helico-radial) has at least one compression stage inclined with respect to said central axis, so that the fluid leaves the compressor impeller at a non-zero angle with the radial direction.
  • a diffuser of a radial compressor is composed of a wheel formed of two flanges between which the gases flow radially or inclined from the center to the periphery.
  • the fins are distributed between the flanges along the wheel. These fins form a flow grid between the leading edges of these fins and the trailing edges.
  • the deflection of the air flow at the exit of the impeller by the fins of the diffuser can cause a detachment of the fluid on the lower surface or the upper surface of the fins, which detachment, as long as it is important, can lead to the stall. fluid and, consequently, pumping. It is known that this pumping phenomenon is harmful to the constituent elements of the compressor, so that we try to avoid it as far as possible.
  • the vanes of the diffuser are constructed from a lower surface and an extrados wall in the shape of a circular arc, and comprise a quasi-linear angle law.
  • An example of such a fin is illustrated in figure 1 .
  • these fins have a limitation in terms of diffusing capacity. Indeed, an increase in the diffusion by these fins causes a drop in isentropic efficiency and an increase in the instability of the compressor.
  • S S -shaped fins of similar profile have also been described in the document JP 2011-252424 .
  • the fins of this document are configured so that an angle formed between the line of curvature and the circumferential profile increases, then decreases, then increases again between the leading edge and the trailing edge of the fin .
  • the section at the neck of the diffuser must be restricted, which has the effect of reducing the stability of the diffuser.
  • An object of the invention is to improve the performance and pumping margin of diffusers of radial and mixed compressors of the prior art.
  • the invention also proposes a diffuser comprising at least one fin as described above, as well as a radial or mixed compressor comprising such a diffuser, and an engine comprising such a compressor.
  • a radial diffuser according to the present invention is particularly intended to be used with a compressor 2 of radial or mixed type.
  • the figure 4 is a partial section of a motor 1 comprising a radial compressor 2.
  • a gas flow F is first drawn into an air inlet sleeve, then compressed between the blades 3a of a wheel 3 of the radial compressor 2 and its crankcase.
  • the compressor 2 is of axial symmetry around an axis X.
  • the compressed gas flow F then exits radially from the wheel 3. If the compressor 2 was mixed, the gas flow would exit inclined at a non-zero angle with respect to a radial direction to the X axis.
  • the compressed air leaves the wheel 3 radially while having a kinetic moment and passes through a diffuser 5.
  • the role of the diffuser 5 is to convert a portion of the kinetic energy of the gas from the compressor 2 in static pressure by slowing the speed of gases, and straighten the flow from the wheel 3. It comprises for this a plurality of fins 10 arranged along its circumference, which extend between a front flange 5a and a rear flange 5b.
  • Each of the fins 10 has, in known manner, a leading edge 11 disposed opposite a gas flow, a trailing edge 12 opposite the leading edge 11, an extrados side wall 13 and a side wall intrados 14 which connect the leading edge 11 to the trailing edge 12.
  • the front flanges 5a and rear 5b may be planar.
  • at least one of the flanges 5a, 5b may comprise, in the space they define between them, at least one zone with alternating curvature between two fins 10, so that the air stream may comprise evolutionary head and foot meridians.
  • the flanges 5a, 5b may be evolutionary shapes axisymmetric.
  • front flanges 5a and 5b rear can be arranged to allow suction and blowing into the diffuser 5.
  • the fin 10 comprises a profile whose camber line 15 has at least two points of inflection I1, I2 between its leading edge 11 and its trailing edge 12, that is to say at least two changes of concavity.
  • the inflection points I1, I2 together define the capture zone, which comprises the portion of the fin 10 extending upstream of the first point of inflection I1, of the diffusion zone, which comprises the part of the fin 10 which extends downstream of the second point of inflection I2.
  • the points of inflection I1, I2 are situated between 10% and 90% of the cord 16, preferably between 30% and 70%. %.
  • a first I1 of the inflection points may be between 35% and 55% of the cord 16, while the second point of inflection I2 is between 55% and 65% of the cord 16.
  • the points I1, I2 may in particular be arranged symmetrically with respect to the center of the rope 16.
  • the profile of the fin 10 may comprise more points of inflection I1, I2.
  • the camber line 15 presents successively at least, between the leading edge 11 and the trailing edge 12, a first concavity, a second concavity different from the first concavity, then a third concavity.
  • the inflection points I1, I2 are symmetrical relative to the center of the rope 16, the second concavity is then centered in the fin 10.
  • the intrados wall 14 and the extrados wall 13 substantially follow the curvature of the camber line 15, and therefore have as many points of inflection I1, I2.
  • the intrados wall 14 and the extrados wall 13 thus comprise two points of inflection I1, I2.
  • the intrados wall 14 comprises a convex portion 14a between the leading edge 11 and the first point of inflection, then a concave portion 14b between the two points of inflection I1, I2, and a convex portion 14c between the second inflection point and the trailing edge 12.
  • the upper surface 13 as for it comprises a concave portion 13a between the leading edge 11 and the first point of inflection, then a convex portion 13b between the two points d I1, I2, then a concave portion 13c between the second inflection point and the trailing edge 12.
  • camber line 15 extends between the intrados wall 14 and the rope 16. In other words, at any point between the leading edge 11 and the trailing edge 12, the line of camber 15 and the intrados wall 14 extend away from the rope 16. In addition, the concave areas of the upper wall 13 pass through the rope 16, and are therefore at least partially on the same side as the line camber 15 of said rope 16.
  • the leading edge 11 and the trailing edge 12 are oriented in the same general direction with respect to the flow of the gas that usually encountered in conventional diffusers, which allows to preserve the cross section, that is to say the inlet section of the fluid between two fins 10 adjacent. In this way, the stability of the diffuser 5 is maintained while improving the diffusion of the flow.
  • the angle of attack ⁇ (which corresponds to the angle between the tangent to the camber line 15 at the leading edge 11 and the rope 16) may be substantially identical to that of the conventional fins.
  • the angle of attack ⁇ can be between about 0 ° and about 45 °. In this way, it is possible to substantially retain the shape of the conventional diffuser fins 5 in their area of capture, thereby preserving the stability of the flow.
  • the presence of the second point of inflection I2 makes it possible to modify the shape of the fins 10 in their diffusion zone to increase the efficiency of the diffuser 5, without modifying the shape of the capture zone.
  • the camber line 15 of the fin profile 10 comprises at least two points of inflection I1, I2.
  • the number of inflection points I1, I2 may be even in order to maintain the general orientation of the leading edge 11 and the trailing edge 12 with respect to the flow, and thus to preserve the neck section.
  • the corresponding camber line 15 again extends between the intrados wall 14 and the rope 16, so that at any point between the leading edge 11 and the 12, the camber line 15 and the intrados wall 14 extend at a distance from the rope 16, and the concave zones of the extrados wall 13 pass through the rope 16.

Landscapes

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

Description

DOMAINE DE L'INVENTIONFIELD OF THE INVENTION

L'invention concerne de manière générale les moteurs à turbine à gaz, et plus particulièrement une ailette d'un diffuseur pour un compresseur radial ou mixte, un étage de diffusion d'un compresseur radial ou mixte d'une turbine à gaz, ainsi qu'à un compresseur associé.The invention relates generally to gas turbine engines, and more particularly to a fin of a diffuser for a radial or mixed compressor, a diffusion stage of a radial or mixed compressor of a gas turbine, and 'to an associated compressor.

ARRIERE-PLAN TECHNOLOGIQUEBACKGROUND

Un compresseur comprend un ou plusieurs disques tournants (rotor ou rouet), aubagés ou non et une ou plusieurs roues à aubes fixes (étages redresseurs).A compressor comprises one or more rotating disks (rotor or wheel), bladed or not and one or more fixed vane wheels (rectifier stages).

Un compresseur radial (ou centrifuge) possède au moins un étage de compression radial, c'est-à-dire apte à réaliser un écoulement de gaz perpendiculaire à l'axe central du compresseur. Il comprend au moins un rouet à pales radiales qui aspirent l'air axialement, qui, sous l'effet de la force radial, est accéléré, comprimé et refoulé radialement. Cet air est ensuite redressé dans un diffuseur (aubage fixe) qui transforme une partie de sa vitesse en pression statique en ralentissant les gaz en sortie du rouet. L'opération doit se dérouler avec un minimum de perte de pression totale tout en maintenant un niveau de stabilité du compresseur satisfaisant afin de maintenir une marge au pompage acceptable pour le fonctionnement de la turbomachine.A radial (or centrifugal) compressor has at least one radial compression stage, that is to say capable of producing a flow of gas perpendicular to the central axis of the compressor. It comprises at least one radial impeller which sucks the air axially, which, under the effect of the radial force, is accelerated, compressed and discharged radially. This air is then straightened in a diffuser (fixed blade) which transforms part of its speed into static pressure by slowing the gases at the exit of the wheel. The operation must take place with a minimum of total pressure loss while maintaining a satisfactory compressor stability level in order to maintain an acceptable pumping margin for the operation of the turbomachine.

Les gaz sont alors guidés vers la chambre de combustion.The gases are then guided to the combustion chamber.

Un compresseur mixte (ou hélico-radial) possède au moins un étage de compression incliné par rapport audit axe central, de sorte que le fluide sort du rouet du compresseur en faisant un angle non nul avec la direction radiale.A mixed compressor (or helico-radial) has at least one compression stage inclined with respect to said central axis, so that the fluid leaves the compressor impeller at a non-zero angle with the radial direction.

Un diffuseur d'un compresseur radial est composé d'une roue formée de deux flasques entre lesquelles s'écoulent les gaz de manière radiale ou inclinée à partir du centre vers la périphérie. Des ailettes sont réparties entre les flasques tout le long de la roue. Ces ailettes forment une grille d'écoulement entre les bords d'attaque de ces ailettes et les bords de fuite.A diffuser of a radial compressor is composed of a wheel formed of two flanges between which the gases flow radially or inclined from the center to the periphery. The fins are distributed between the flanges along the wheel. These fins form a flow grid between the leading edges of these fins and the trailing edges.

Cependant, la déviation du flux d'air en sortie du rouet par les ailettes du diffuseur peut provoquer un décollement du fluide sur l'intrados ou l'extrados des ailettes, lequel décollement, dès lors qu'il est important, peut conduire au décrochage du fluide et, par suite, au pompage. Il est connu que ce phénomène de pompage est néfaste pour les éléments constitutifs du compresseur, en sorte qu'on cherche à l'éviter dans la mesure du possible.However, the deflection of the air flow at the exit of the impeller by the fins of the diffuser can cause a detachment of the fluid on the lower surface or the upper surface of the fins, which detachment, as long as it is important, can lead to the stall. fluid and, consequently, pumping. It is known that this pumping phenomenon is harmful to the constituent elements of the compressor, so that we try to avoid it as far as possible.

Habituellement, les ailettes du diffuseur sont construites à partir d'une paroi intrados et d'une paroi extrados en forme d'arc de cercle, et comprennent une loi d'angle quasi linéaire. Un exemple d'une telle ailette est illustré en figure 1. Cependant, ces ailettes présentent une limitation en termes de capacité diffusante. En effet, une augmentation de la diffusion par ces ailettes provoque une chute de rendement isentropique et un accroissement de l'instabilité du compresseur.Usually, the vanes of the diffuser are constructed from a lower surface and an extrados wall in the shape of a circular arc, and comprise a quasi-linear angle law. An example of such a fin is illustrated in figure 1 . However, these fins have a limitation in terms of diffusing capacity. Indeed, an increase in the diffusion by these fins causes a drop in isentropic efficiency and an increase in the instability of the compressor.

Il a été proposé dans le document WO 2012/019650 un diffuseur pour un compresseur radial comprenant des ailettes conformes au préambule de la revendication 1. En particulier, ce document décrit des ailettes dont le profil présente une ligne de cambrure définie par une fonction ayant un point d'inflexion. La ligne de cambrure présente à cet effet une forme de « S », et permet de distribuer les charges le long du profil de l'ailette, avec un faible chargement dans la zone du bord d'attaque, qui augmente progressivement jusqu'au point d'inflexion de l'ailette où il devient maximal. Cependant, la mise en oeuvre d'une ailette présentant un tel profilé en « S » nécessite de restreindre la section au col du diffuseur (c'est-à-dire la section d'entrée du fluide). Ceci a pour effet de décaler la caractéristique Débit/Taux vers de plus faibles débits, et réduit le débit de blocage aérodynamique du diffuseur.It was proposed in the document WO 2012/019650 a diffuser for a radial compressor comprising fins conforming to the preamble of claim 1. In particular, this document describes fins whose profile has a camber line defined by a function having a point of inflection. The camber line has an "S" shape for this purpose, and allows the loads to be distributed along the fin profile, with low loading in the leading edge area, which progressively increases to the point of inflection of the fin where it becomes maximal. However, the implementation of a fin having such an "S" profile requires restricting the section at the neck of the diffuser (that is to say the inlet section of the fluid). This has the effect of shifting the Flow / Rate characteristic to lower flow rates, and reduces the aerodynamic blocking flow of the diffuser.

Des ailettes de profilé similaire en forme de « S » ont également été décrites dans le document JP 2011-252424 . En particulier, les ailettes de ce document sont configurées de sorte qu'un angle formé entre la ligne de courbure et le profilé circonférentiel augmente, puis diminue, puis augmente à nouveau entre le bord d'attaque et le bord de fuite de l'ailette. Ici encore, la section au col du diffuseur doit donc être restreinte, ce qui a pour effet réduire la stabilité du diffuseur."S" -shaped fins of similar profile have also been described in the document JP 2011-252424 . In particular, the fins of this document are configured so that an angle formed between the line of curvature and the circumferential profile increases, then decreases, then increases again between the leading edge and the trailing edge of the fin . Here again, the section at the neck of the diffuser must be restricted, which has the effect of reducing the stability of the diffuser.

RESUME DE L'INVENTIONSUMMARY OF THE INVENTION

Un objectif de l'invention est d'améliorer les performances et la marge au pompage des diffuseurs des compresseurs radiaux et mixtes de l'art antérieur.An object of the invention is to improve the performance and pumping margin of diffusers of radial and mixed compressors of the prior art.

En particulier, l'invention a pour objectif de proposer un diffuseur d'un compresseur radial ou mixte capable de limiter la chute du rendement isentropique du compresseur et d'améliorer la capacité à ralentir et à redresser l'écoulement délivré par le rouet du compresseur tout en maintenant la stabilité de cet écoulement.
Pour cela, l'invention propose une ailette d'un diffuseur pour un compresseur radial ou mixte d'un moteur, comprenant un bord d'attaque disposé en regard d'un écoulement de gaz, un bord de fuite opposé au bord d'attaque, d'une paroi latérale d'intrados et d'une paroi latérale d'extrados qui relient le bord d'attaque au bord de fuite. Le profil de l'ailette comprend une ligne de cambrure présentant au moins deux points d'inflexion entre le bord d'attaque et le bord de fuite. La courbure de la paroi d'intrados et la courbure de la paroi d'extrados suivent par ailleurs sensiblement la courbure de la ligne de cambrure, de sorte que :

  • la paroi d'intrados comprend, entre le bord d'attaque et le bord de fuite, au moins deux parties convexes séparées par une partie concave, et
  • la paroi d'extrados comprend, entre le bord d'attaque et le bord de fuite, au moins deux parties concaves séparées par une partie convexe, et le profil définit une corde qui s'étend entre le bord d'attaque et le bord de fuite, et les parties convexes de la paroi d'intrados et les parties concaves de la paroi d'extrados s'étendent au moins partiellement du même côté de ladite corde.
In particular, the invention aims to provide a diffuser of a radial or mixed compressor capable of limiting the fall of the isentropic efficiency of the compressor and improve the ability to slow down and straighten the flow delivered by the impeller of the compressor while maintaining the stability of this flow.
For this, the invention proposes a fin of a diffuser for a radial or mixed compressor of a motor, comprising a leading edge disposed opposite a gas flow, a trailing edge opposite the leading edge. , a lower side wall and an extrados side wall which connect the leading edge to the trailing edge. The fin profile includes a camber line having at least two points of inflection between the leading edge and the trailing edge. The curvature of the intrados wall and the curvature of the extrados wall also substantially follow the curvature of the camber line, so that:
  • the intrados wall comprises, between the leading edge and the trailing edge, at least two convex parts separated by a concave part, and
  • the upper surface comprises, between the leading edge and the trailing edge, at least two concave parts separated by a convex part, and the profile defines a rope which extends between the leading edge and the edge of leakage, and the convex portions of the intrados wall and the concave portions of the extrados wall extend at least partially on the same side of said rope.

L'invention propose également un diffuseur comprenant au moins une ailette comme décrit ci-dessus, ainsi qu'un compresseur radial ou mixte comprenant un tel diffuseur, et un moteur comprenant un tel compresseur.The invention also proposes a diffuser comprising at least one fin as described above, as well as a radial or mixed compressor comprising such a diffuser, and an engine comprising such a compressor.

BREVE DESCRIPTION DES DESSINSBRIEF DESCRIPTION OF THE DRAWINGS

D'autres caractéristiques, buts et avantages de la présente invention apparaîtront mieux à la lecture de la description détaillée qui va suivre, et au regard des dessins annexés donnés à titre d'exemples non limitatifs et sur lesquels :

  • La figure 1 illustre un exemple de profil de pales d'un diffuseur conforme à l'art antérieur,
  • La figure 2 illustre un exemple de profil de pales d'un diffuseur conforme à l'invention,
  • La figure 3 est une vue en détail d'une pale de la figure 2, sur laquelle a été représentée une corde et une ligne médiane de la pale, et
  • La figure 4 illustre un exemple de moteur pouvant comprendre un diffuseur conforme à l'invention.
Other features, objects and advantages of the present invention will appear better on reading the detailed description which follows, and with reference to the appended drawings given by way of non-limiting examples and in which:
  • The figure 1 illustrates an example of blade profile of a diffuser according to the prior art,
  • The figure 2 illustrates an example of blade profile of a diffuser according to the invention,
  • The figure 3 is a detailed view of a blade of the figure 2 , on which has been represented a rope and a median line of the blade, and
  • The figure 4 illustrates an example of an engine that may include a diffuser according to the invention.

DESCRIPTION DETAILLEE D'UN MODE DE REALISATIONDETAILED DESCRIPTION OF AN EMBODIMENT

Un diffuseur radial selon la présente invention est notamment destiné à être utilisé avec un compresseur 2 de type radial ou mixte.A radial diffuser according to the present invention is particularly intended to be used with a compressor 2 of radial or mixed type.

La figure 4 est une coupe partielle d'un moteur 1 comportant un compresseur radial 2. Un flux gazeux F est d'abord aspiré dans une manche d'entrée d'air, puis comprimé entre les pales 3a d'un rouet 3 du compresseur radial 2 et son carter. Le compresseur 2 est de symétrie axiale autour d'un axe X. Le flux gazeux F comprimé sort alors radialement du rouet 3. Si le compresseur 2 était mixte, le flux gazeux sortirait incliné selon un angle non nul par rapport à une direction radiale à l'axe X.The figure 4 is a partial section of a motor 1 comprising a radial compressor 2. A gas flow F is first drawn into an air inlet sleeve, then compressed between the blades 3a of a wheel 3 of the radial compressor 2 and its crankcase. The compressor 2 is of axial symmetry around an axis X. The compressed gas flow F then exits radially from the wheel 3. If the compressor 2 was mixed, the gas flow would exit inclined at a non-zero angle with respect to a radial direction to the X axis.

L'air comprimé sort radialement du rouet 3 tout en présentant un moment cinétique et passe dans un diffuseur 5. Le rôle du diffuseur 5 est de convertir une partie de l'énergie cinétique des gaz en provenance du compresseur 2 en pression statique en ralentissant la vitesse des gaz, et de redresser l'écoulement issu du rouet 3. Il comprend pour cela une pluralité d'ailettes 10 disposées selon sa circonférence, qui s'étendent entre un flasque avant 5a et un flasque arrière 5b. Chacune des ailettes 10 présente, de manière connue, un bord d'attaque 11 disposé en regard d'un écoulement de gaz, un bord de fuite 12 opposé au bord d'attaque 11, une paroi latérale d'extrados 13 et une paroi latérale d'intrados 14 qui relient le bord d'attaque 11 au bord de fuite 12.The compressed air leaves the wheel 3 radially while having a kinetic moment and passes through a diffuser 5. The role of the diffuser 5 is to convert a portion of the kinetic energy of the gas from the compressor 2 in static pressure by slowing the speed of gases, and straighten the flow from the wheel 3. It comprises for this a plurality of fins 10 arranged along its circumference, which extend between a front flange 5a and a rear flange 5b. Each of the fins 10 has, in known manner, a leading edge 11 disposed opposite a gas flow, a trailing edge 12 opposite the leading edge 11, an extrados side wall 13 and a side wall intrados 14 which connect the leading edge 11 to the trailing edge 12.

Les flasques avant 5a et arrière 5b peuvent être plans. En variante, l'un au moins des flasques 5a, 5b peut comprendre, dans l'espace qu'ils définissent entre eux, au moins une zone à courbure alternée entre deux ailettes 10, de sorte que la veine d'air peut comprendre des méridiennes tête et pied évolutives. On pourra se référer au document FR 2 976 633 au nom de la Demanderesse pour plus de détail sur les flasques avant 5a et/ou arrière 5b présentant une telle courbure alternée.The front flanges 5a and rear 5b may be planar. In a variant, at least one of the flanges 5a, 5b may comprise, in the space they define between them, at least one zone with alternating curvature between two fins 10, so that the air stream may comprise evolutionary head and foot meridians. We can refer to the document FR 2,976,633 in the name of the Applicant for more details on the front flanges 5a and / or rear 5b having such an alternating curvature.

Selon une autre variante encore, les flasques 5a, 5b peuvent être à formes évolutives axisymétriques.According to another variant, the flanges 5a, 5b may be evolutionary shapes axisymmetric.

Par ailleurs, les flasques avant 5a et arrière 5b peuvent être aménagés de manière à permettre l'aspiration et le soufflage dans le diffuseur 5.Furthermore, the front flanges 5a and 5b rear can be arranged to allow suction and blowing into the diffuser 5.

Au moins l'une des ailettes 10 du diffuseur 5, de préférence l'ensemble des ailettes 10, comprend, d'amont en aval dans le sens de l'écoulement des gaz :

  • une première zone, dite de captation, dont la forme est configurée pour s'adapter à l'écoulement amont, et
  • une deuxième zone, dite de diffusion, dont la forme est configurée pour redresser plus fortement l'écoulement en provenance de la zone de captation, afin d'obtenir une pression statique plus importante en sortie du diffuseur 5 et de faciliter l'alimentation de la pièce aval, généralement un diffuseur 5 axial.
At least one of the fins 10 of the diffuser 5, preferably all of the fins 10, comprises, from upstream to downstream in the direction of the gas flow:
  • a first zone, said capture zone, whose shape is configured to adapt to the upstream flow, and
  • a second zone, called diffusion zone, the shape of which is configured to straighten more strongly the flow coming from the capture zone, in order to obtain a greater static pressure at the diffuser outlet 5 and to facilitate the feeding of the downstream part, usually an axial diffuser.

L'ailette 10 comprend un profil dont la ligne de cambrure 15 présente au moins deux points d'inflexion I1, I2 entre son bord d'attaque 11 et son bord de fuite 12, c'est-à-dire au moins deux changements de concavité.The fin 10 comprises a profile whose camber line 15 has at least two points of inflection I1, I2 between its leading edge 11 and its trailing edge 12, that is to say at least two changes of concavity.

Dans ce qui suit, on comprendra par « point d'inflexion » un point d'une courbe au niveau duquel la courbe traverse sa tangente. Par ailleurs, par profil de l'ailette 10, on comprendra ici une section transversale de l'ailette 10, c'est-à-dire une section de l'ailette 10 selon un plan globalement perpendiculaire à l'extrados 13 et à l'intrados 14 de l'ailette 10. Enfin, la « ligne de cambrure 15 » du profil correspond à la ligne fictive qui comprend l'ensemble des points équidistants de l'extrados 13 et de l'intrados 14 de l'ailette 10, tandis que la « corde 16 » correspond au segment qui a pour extrémités le bord d'attaque 11 et le bord de fuite 12.In what follows, we will understand by "point of inflection" a point of a curve at which the curve crosses its tangent. Furthermore, by profile of the fin 10, here will be understood a cross section of the fin 10, that is to say a section of the fin 10 in a plane generally perpendicular to the upper surface 13 and the upper surface. the intrados 14 of the fin 10. Finally, the "camber line 15" of the profile corresponds to the imaginary line which comprises all the equidistant points of the upper surface 13 and the lower surface 14 of the fin 10, while the "rope 16" corresponds to the segment which ends with the leading edge 11 and the trailing edge 12.

Les points d'inflexion I1, I2 délimitent ensemble la zone de captation, qui comprend la partie de l'ailette 10 s'étendant en amont du premier point d'inflexion I1, de la zone de diffusion, qui comprend la partie de l'ailette 10 qui s'étend en aval du deuxième point d'inflexion I2.The inflection points I1, I2 together define the capture zone, which comprises the portion of the fin 10 extending upstream of the first point of inflection I1, of the diffusion zone, which comprises the part of the fin 10 which extends downstream of the second point of inflection I2.

De préférence, afin d'optimiser la stabilité du diffuseur 5 et la pression statique en sortie du diffuseur 5, les points d'inflexion I1, I2 sont situés entre 10% et 90% de la corde 16, de préférence entre 30% et 70%. Par exemple, un premier I1 des points d'inflexion peut être situé entre 35% et 55% de la corde 16, tandis que le deuxième point d'inflexion I2 est situé entre 55% et 65% de la corde 16. Les points d'inflexion I1, I2 peuvent en particulier être disposés symétriquement par rapport au centre de la corde 16.Preferably, in order to optimize the stability of the diffuser 5 and the static pressure at the outlet of the diffuser 5, the points of inflection I1, I2 are situated between 10% and 90% of the cord 16, preferably between 30% and 70%. %. For example, a first I1 of the inflection points may be between 35% and 55% of the cord 16, while the second point of inflection I2 is between 55% and 65% of the cord 16. The points I1, I2 may in particular be arranged symmetrically with respect to the center of the rope 16.

En variante, le profil de l'ailette 10 peut comprendre davantage de points d'inflexion I1, I2.Alternatively, the profile of the fin 10 may comprise more points of inflection I1, I2.

Ainsi, la ligne de cambrure 15 présente successivement au moins, entre le bord d'attaque 11 et le bord de fuite 12, une première concavité, une deuxième concavité différente de la première concavité, puis une troisième concavité. Lorsque les points d'inflexion I1, I2 sont symétriques par rapport au centre de la corde 16, la deuxième concavité est alors centrée dans l'ailette 10.Thus, the camber line 15 presents successively at least, between the leading edge 11 and the trailing edge 12, a first concavity, a second concavity different from the first concavity, then a third concavity. When the inflection points I1, I2 are symmetrical relative to the center of the rope 16, the second concavity is then centered in the fin 10.

Selon l'invention la paroi d'intrados 14 et la paroi d'extrados 13 suivent sensiblement la courbure de la ligne de cambrure 15, et présentent donc autant de points d'inflexion I1, I2.According to the invention the intrados wall 14 and the extrados wall 13 substantially follow the curvature of the camber line 15, and therefore have as many points of inflection I1, I2.

Comme illustré sur les figures 2 et 3, la paroi d'intrados 14 et la paroi d'extrados 13 comprennent donc deux points d'inflexion I1, I2. La paroi d'intrados 14 comprend une partie convexe 14a entre le bord d'attaque 11 et le premier point d'inflexion, puis une partie concave 14b entre les deux points d'inflexion I1, I2, puis une partie convexe 14c entre le deuxième point d'inflexion et le bord de fuite 12. La paroi d'extrados 13 quant à elle comprend une partie concave 13a entre le bord d'attaque 11 et le premier point d'inflexion, puis une partie convexe 13b entre les deux points d'inflexion I1, I2, puis une partie concave 13c entre le deuxième point d'inflexion et le bord de fuite 12.As illustrated on figures 2 and 3 , the intrados wall 14 and the extrados wall 13 thus comprise two points of inflection I1, I2. The intrados wall 14 comprises a convex portion 14a between the leading edge 11 and the first point of inflection, then a concave portion 14b between the two points of inflection I1, I2, and a convex portion 14c between the second inflection point and the trailing edge 12. The upper surface 13 as for it comprises a concave portion 13a between the leading edge 11 and the first point of inflection, then a convex portion 13b between the two points d I1, I2, then a concave portion 13c between the second inflection point and the trailing edge 12.

Par ailleurs, la ligne de cambrure 15 s'étend entre la paroi d'intrados 14 et la corde 16. En d'autres termes, en tout point entre le bord d'attaque 11 et le bord de fuite 12, la ligne de cambrure 15 et la paroi d'intrados 14 s'étendent à distance de la corde 16. De plus, les zones concaves de la paroi d'extrados 13 traversent la corde 16, et se trouvent par conséquent au moins partiellement du même côté que la ligne de cambrure 15 de ladite corde 16.Furthermore, the camber line 15 extends between the intrados wall 14 and the rope 16. In other words, at any point between the leading edge 11 and the trailing edge 12, the line of camber 15 and the intrados wall 14 extend away from the rope 16. In addition, the concave areas of the upper wall 13 pass through the rope 16, and are therefore at least partially on the same side as the line camber 15 of said rope 16.

Grâce à cette configuration, rendue possible par les deux points d'inflexion I1, I2 de la ligne de cambrure 15, le bord d'attaque 11 et le bord de fuite 12 sont orientés dans le même sens général par rapport à l'écoulement des gaz que celui rencontré habituellement dans les diffuseurs 5 conventionnels, ce qui permet de préserver la section au col, c'est-à-dire la section d'entrée du fluide entre deux ailettes 10 adjacentes. De la sorte, la stabilité du diffuseur 5 est conservée tout en améliorant la diffusion de l'écoulement.Thanks to this configuration, made possible by the two points of inflection I1, I2 of the camber line 15, the leading edge 11 and the trailing edge 12 are oriented in the same general direction with respect to the flow of the gas that usually encountered in conventional diffusers, which allows to preserve the cross section, that is to say the inlet section of the fluid between two fins 10 adjacent. In this way, the stability of the diffuser 5 is maintained while improving the diffusion of the flow.

L'angle d'attaque α (qui correspond à l'angle entre la tangente à la ligne de cambrure 15 au niveau du bord d'attaque 11 et la corde 16) peut être sensiblement identique à celui des ailettes 10 conventionnelles. Par exemple, l'angle d'attaque α peut être compris entre environ 0° et environ 45°. De la sorte, il est possible de conserver sensiblement la forme des ailettes 10 de diffuseurs 5 conventionnelles dans leur zone de captation, ce qui permet de préserver la stabilité de l'écoulement. De plus, la présence du deuxième point d'inflexion I2 permet de modifier la forme des ailettes 10 dans leur zone de diffusion pour augmenter le rendement du diffuseur 5, sans pour autant modifier la forme de la zone de captation. En effet, il est à présent possible d'augmenter l'angle entre la ligne de cambrure 15 au niveau du bord de fuite 12 et la corde 16, indépendamment de la forme de la zone de captation, ce qui permet de redresser plus fortement l'écoulement des gaz et donc d'augmenter la pression statique et le taux de pression totale à iso-échauffement en sortie du diffuseur 5, et donc d'améliorer le rendement isentropique du diffuseur 5 tout en maintenant la marge au pompage et donc la stabilité du compresseur 2.The angle of attack α (which corresponds to the angle between the tangent to the camber line 15 at the leading edge 11 and the rope 16) may be substantially identical to that of the conventional fins. For example, the angle of attack α can be between about 0 ° and about 45 °. In this way, it is possible to substantially retain the shape of the conventional diffuser fins 5 in their area of capture, thereby preserving the stability of the flow. In addition, the presence of the second point of inflection I2 makes it possible to modify the shape of the fins 10 in their diffusion zone to increase the efficiency of the diffuser 5, without modifying the shape of the capture zone. Indeed, it is now possible to increase the angle between the camber line 15 at the trailing edge 12 and the rope 16, regardless of the shape of the capture area, which allows to straighten more strongly. the flow of gases and therefore increase the static pressure and the total pressure ratio iso-heating output of the diffuser 5, and thus improve the isentropic efficiency of the diffuser 5 while maintaining the margin pumping and therefore the stability compressor 2.

Comme indiqué précédemment, la ligne de cambrure 15 du profil de l'ailette 10 comprend au moins deux points d'inflexion I1, I2. De préférence, le nombre de points d'inflexion I1, I2 peut être pair afin de conserver l'orientation générale du bord d'attaque 11 et du bord de fuite 12 par rapport à l'écoulement, et donc de préserver section au col. Par ailleurs, selon r l'invention, la ligne de cambrure 15 correspondante s'étend ici encore entre la paroi d'intrados 14 et la corde 16, de sorte que, en tout point entre le bord d'attaque 11 et le bord de fuite 12, la ligne de cambrure 15 et la paroi d'intrados 14 s'étendent à distance de la corde 16, et les zones concaves de la paroi d'extrados 13 traversent la corde 16.As indicated above, the camber line 15 of the fin profile 10 comprises at least two points of inflection I1, I2. Preferably, the number of inflection points I1, I2 may be even in order to maintain the general orientation of the leading edge 11 and the trailing edge 12 with respect to the flow, and thus to preserve the neck section. Furthermore, according to the invention, the corresponding camber line 15 again extends between the intrados wall 14 and the rope 16, so that at any point between the leading edge 11 and the 12, the camber line 15 and the intrados wall 14 extend at a distance from the rope 16, and the concave zones of the extrados wall 13 pass through the rope 16.

Claims (8)

  1. A vane (10) of a diffuser (5) for a radial or mixed-flow compressor (2) of an engine (1), including a leading edge (11) positioned facing a gas flow, a trailing edge (12) opposite to the leading edge (11), an extrados side wall (13) and an intrados side wall (14) which connect the leading edge (11) to the trailing edge (12),
    the vane (10) including a profile having a camber line (15) with at least two inflection points (I1, I2) between the leading edge (11) and the trailing edge (12),
    the vane being characterized in that the curve of the intrados wall (14) and the curve of the extrados wall (13) substantially follow the curve of the camber line (15), so that:
    - the intrados wall (14) includes, between the leading edge (11) and the trailing edge (12), at least two convex parts (14a, 14c) separated by a concave part (14b), and
    - the extrados wall (13) includes, between the leading edge (11) and the trailing edge (12), at least two concave parts (13a, 13c) separated by a convex part (13b),
    and in that the profile defines a chord (16) which extends between the leading edge (11) and the trailing edge (12), and the convex parts (14a, 14c) of the intrados wall (14) and the concave parts (13a, 13c) of the extrados wall (13) extend at least partially on the same side of said chord (16).
  2. The vane (10) according to claim 1, wherein the profile defines a chord (16) which extends between the leading edge (11) and the trailing edge (12) and, at every point between the leading edge (11) and the trailing edge (12), said chord (16) is located remotely from the camber line (15).
  3. The vane (10) according to one of claims 1 or 2, wherein the profile defines a chord (16) which extends between the leading edge (11) and the trailing edge (12), and the inflection points (I1, I2) are located between 10% and 90% of said chord (16).
  4. The vane (10) according to claim 3, wherein a first (I1) of said inflection points is located between 35% and 55% of the chord (16), and a second (I2) of said inflection point is located between 55% and 65% of said chord (16).
  5. The vane (10) according to one of claims 1 to 4, including an angle of attack (α) comprised between about 0° and about 45°.
  6. A diffuser (5) of a radial or mixed-flow compressor of an engine (1) including at least one vane (10) according to one of claims 1 to 5.
  7. A radial or mixed-flow compressor (2) of an engine (1), including a diffuser (5) according to claim 6.
  8. An engine (1), including a radial or mixed-flow compressor (2) according to claim 7.
EP14718669.6A 2013-03-28 2014-03-25 Vane for radial or mixed-flow compressor Active EP2978977B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1352829A FR3003908B1 (en) 2013-03-28 2013-03-28 DIFFUSER WITH FINES OF A RADIAL OR MIXED COMPRESSOR
PCT/FR2014/050693 WO2014154997A1 (en) 2013-03-28 2014-03-25 Radial or mixed-flow compressor diffuser having vanes

Publications (2)

Publication Number Publication Date
EP2978977A1 EP2978977A1 (en) 2016-02-03
EP2978977B1 true EP2978977B1 (en) 2016-10-19

Family

ID=48901098

Family Applications (1)

Application Number Title Priority Date Filing Date
EP14718669.6A Active EP2978977B1 (en) 2013-03-28 2014-03-25 Vane for radial or mixed-flow compressor

Country Status (11)

Country Link
US (1) US9890792B2 (en)
EP (1) EP2978977B1 (en)
JP (1) JP6367917B2 (en)
KR (1) KR102196815B1 (en)
CN (1) CN105247223B (en)
CA (1) CA2908081C (en)
ES (1) ES2606831T3 (en)
FR (1) FR3003908B1 (en)
PL (1) PL2978977T3 (en)
RU (1) RU2651905C2 (en)
WO (1) WO2014154997A1 (en)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102014221362A1 (en) 2014-10-21 2016-04-21 Siemens Aktiengesellschaft Profiling of vanes of nozzles in turbomachinery, in particular compressors
DE102015107907A1 (en) * 2015-05-20 2016-11-24 Ebm-Papst Mulfingen Gmbh & Co. Kg Eben Strömungsleitgitter
US9732775B2 (en) * 2015-06-24 2017-08-15 The Boeing Company Flow straightener apparatus and systems for ducted air
KR101848437B1 (en) * 2017-03-28 2018-04-13 한국과학기술연구원 Centrifugal turbo machinery having flexibly variable diffuser vane
KR102083168B1 (en) * 2017-11-07 2020-03-02 주식회사 에어로네트 Impeller having primary blades and secondary blades
KR102427392B1 (en) * 2018-01-24 2022-07-29 한화에어로스페이스 주식회사 Diffuser for compressor
US11421708B2 (en) 2018-03-16 2022-08-23 Carrier Corporation Refrigeration system mixed-flow compressor
KR102095835B1 (en) 2019-01-25 2020-04-01 (주)대주기계 Industrial diffuser with a wavy rotating cylinder
US10989219B2 (en) 2019-02-04 2021-04-27 Honeywell International Inc. Diffuser assemblies for compression systems
US11098730B2 (en) * 2019-04-12 2021-08-24 Rolls-Royce Corporation Deswirler assembly for a centrifugal compressor
CN112651117B (en) * 2020-12-21 2023-03-28 贵州电网有限责任公司 Dynamic segmental closing method for guide vane of hydroelectric generating set
CN113339267B (en) * 2021-06-17 2022-07-26 清华大学 Cambered high-energy-density blade design method and vane pump designed by same

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3298636A (en) * 1965-01-15 1967-01-17 Arnholdt Eric Airfoil
SU1409785A2 (en) * 1986-12-23 1988-07-15 Университет дружбы народов им.Патриса Лумумбы Vaned diffusor of centrifugal compressor
US5395071A (en) * 1993-09-09 1995-03-07 Felix; Frederick L. Airfoil with bicambered surface
JP3948785B2 (en) 1996-05-17 2007-07-25 カルソニックカンセイ株式会社 Centrifugal multiblade fan
FR2937385B1 (en) * 2008-10-17 2010-12-10 Turbomeca DIFFUSER WITH AUBES A ORIFICES
CN101865145B (en) * 2009-04-20 2012-09-19 日立空调·家用电器株式会社 Electric blower, electric dust collector carrying the same and manufacturing method thereof
EP2299124A1 (en) 2009-09-04 2011-03-23 Siemens Aktiengesellschaft Rotor blade for an axial compressor
FR2958967B1 (en) * 2010-04-14 2013-03-15 Turbomeca METHOD FOR ADJUSTING TURBOMACHINE AIR FLOW WITH CENTRIFUGAL COMPRESSOR AND DIFFUSER THEREFOR
JP5299354B2 (en) * 2010-06-01 2013-09-25 株式会社日立プラントテクノロジー Turbo fluid machine
US8834104B2 (en) * 2010-06-25 2014-09-16 Honeywell International Inc. Vanes for directing exhaust to a turbine wheel
CA2811348A1 (en) * 2010-08-12 2012-02-16 Nuovo Pignone S.P.A. Radial diffuser vane for centrifugal compressors
FR2976633B1 (en) 2011-06-20 2015-01-09 Turbomeca METHOD OF DIFFUSING A COMPRESSION STAGE OF A GAS TURBINE AND THE DIFFUSION STAGE THEREFOR

Non-Patent Citations (1)

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

Also Published As

Publication number Publication date
KR20150138291A (en) 2015-12-09
RU2015146262A3 (en) 2018-03-01
CA2908081A1 (en) 2014-10-02
JP6367917B2 (en) 2018-08-01
KR102196815B1 (en) 2020-12-30
FR3003908B1 (en) 2017-07-07
ES2606831T3 (en) 2017-03-28
RU2651905C2 (en) 2018-04-24
CN105247223B (en) 2017-05-17
US20160053774A1 (en) 2016-02-25
JP2016514791A (en) 2016-05-23
EP2978977A1 (en) 2016-02-03
FR3003908A1 (en) 2014-10-03
CN105247223A (en) 2016-01-13
WO2014154997A1 (en) 2014-10-02
US9890792B2 (en) 2018-02-13
RU2015146262A (en) 2017-05-04
PL2978977T3 (en) 2017-02-28
CA2908081C (en) 2020-11-24

Similar Documents

Publication Publication Date Title
EP2978977B1 (en) Vane for radial or mixed-flow compressor
EP1916385B1 (en) Sponson of fan platform
CA2826153C (en) Blade-platform assembly for subsonic flow
EP2710268B1 (en) Gas turbine diffuser blowing method and corresponding diffuser
EP2438306B1 (en) Centrifugal impeller of compressor
FR3062431A1 (en) TURBOMACHINE ROTARY BLADE, INCLUDING A HITCH AT THE TOP AND ON THE EDGE OF ATTACK
EP2582986B1 (en) Aerodynamic coupling between two annular rows of stationary vanes in a turbine engine
WO2018185445A1 (en) Reinforced axial diffuser
FR2958346A1 (en) Compressor for turboshaft engine i.e. turbomotor, of helicopter, has straightening vane comprising upstream portion that is arranged such that bottom-surface of portion includes profile that is concave in transverse plane of vane
EP2721305B1 (en) Method for diffusing a gas turbine compression stage, and diffusion stage for implementing same
WO2013132190A1 (en) Vortex generators placed in the interblade channel of a compressor rectifier
FR3089576A1 (en) Centrifugal impeller
FR3065759A1 (en) CENTRIFUGAL ROLLER FOR TURBOMACHINE
WO2024033065A1 (en) Variable vane of an aircraft turbine engine stator, and aircraft turbine engine
EP4100625A1 (en) Rotor blade for a turbomachine
FR3009348B1 (en) DIFFUSER FOR A RADIAL OR MIXED COMPRESSOR OF AN ENGINE COMPRISING A FLASK OF WHICH A PART IS MOBILE
FR3027354B1 (en) AUBES WHEEL COMPRISING DRILLING BETWEEN THE INTRADOS AND THE EXTRADOS OF THE DAWN AND ASSOCIATED MOTOR

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: 20151027

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

AX Request for extension of the european patent

Extension state: BA ME

RIN1 Information on inventor provided before grant (corrected)

Inventor name: TARNOWSKI, LAURENT

Inventor name: BULOT, NICOLAS

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

INTG Intention to grant announced

Effective date: 20160812

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

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: 838605

Country of ref document: AT

Kind code of ref document: T

Effective date: 20161115

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: 602014004377

Country of ref document: DE

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

RAP2 Party data changed (patent owner data changed or rights of a patent transferred)

Owner name: SAFRAN HELICOPTER ENGINES

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 4

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20161019

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: 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: 20161019

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 838605

Country of ref document: AT

Kind code of ref document: T

Effective date: 20161019

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: 20170120

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: 20161019

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: 20170119

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

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: 20170220

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: 20170219

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: 20161019

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: 20161019

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: 20161019

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: 20161019

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: 20161019

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602014004377

Country of ref document: DE

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

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: 20161019

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: 20161019

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: 20161019

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: 20161019

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: 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: 20170119

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: 20161019

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN HELICOPTER ENGINES, FR

Effective date: 20170727

26N No opposition filed

Effective date: 20170720

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: 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: 20161019

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: 20161019

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

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: 20170325

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 5

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

Ref country code: LI

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

Effective date: 20170331

Ref country code: IE

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

Effective date: 20170325

Ref country code: CH

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

Effective date: 20170331

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20170331

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: 20170331

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: 20161019

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

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: 20140325

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: 20161019

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: 20161019

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: 20161019

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

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: 20161019

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

Ref country code: GB

Payment date: 20220225

Year of fee payment: 9

Ref country code: DE

Payment date: 20220217

Year of fee payment: 9

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

Ref country code: SE

Payment date: 20220217

Year of fee payment: 9

Ref country code: PL

Payment date: 20220222

Year of fee payment: 9

Ref country code: IT

Payment date: 20220217

Year of fee payment: 9

Ref country code: CZ

Payment date: 20220223

Year of fee payment: 9

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

Ref country code: ES

Payment date: 20220401

Year of fee payment: 9

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 602014004377

Country of ref document: DE

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: 20230325

REG Reference to a national code

Ref country code: SE

Ref legal event code: EUG

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20230325

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

Ref country code: GB

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

Effective date: 20230325

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

Ref country code: SE

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

Effective date: 20230326

Ref country code: GB

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

Effective date: 20230325

Ref country code: DE

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

Effective date: 20231003

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

Ref country code: IT

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

Effective date: 20230325

REG Reference to a national code

Ref country code: ES

Ref legal event code: FD2A

Effective date: 20240529

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

Ref country code: FR

Payment date: 20240221

Year of fee payment: 11