EP2715146B1 - Centrifugal compressor impeller - Google Patents
Centrifugal compressor impeller Download PDFInfo
- Publication number
- EP2715146B1 EP2715146B1 EP12728683.9A EP12728683A EP2715146B1 EP 2715146 B1 EP2715146 B1 EP 2715146B1 EP 12728683 A EP12728683 A EP 12728683A EP 2715146 B1 EP2715146 B1 EP 2715146B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- impeller
- centrifugal compressor
- wheel
- web
- blades
- 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
Links
- 239000012530 fluid Substances 0.000 claims description 23
- 238000005452 bending Methods 0.000 description 10
- 238000002485 combustion reaction Methods 0.000 description 8
- 240000006108 Allium ampeloprasum Species 0.000 description 6
- 235000005254 Allium ampeloprasum Nutrition 0.000 description 6
- 230000002093 peripheral effect Effects 0.000 description 4
- 210000003462 vein Anatomy 0.000 description 4
- 230000006835 compression Effects 0.000 description 3
- 238000007906 compression Methods 0.000 description 3
- 238000006073 displacement reaction Methods 0.000 description 3
- 238000011144 upstream manufacturing Methods 0.000 description 3
- 239000000446 fuel Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000009987 spinning Methods 0.000 description 2
- 239000004215 Carbon black (E152) Substances 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 229930195733 hydrocarbon Natural products 0.000 description 1
- 150000002430 hydrocarbons Chemical class 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
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
- F04D29/26—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
-
- 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
- F04D29/288—Part of the wheel having an ejecting effect, e.g. being bladeless diffuser
-
- 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
- F04D29/40—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
- 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
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/70—Shape
Definitions
- the present invention relates to the field of centrifugal compressors.
- the invention more particularly relates to a centrifugal compressor wheel comprising a web and vanes integral with the web on a front face of the web, each having a leading edge and a trailing edge, and a centrifugal compressor comprising such a wheel , and a turbomachine comprising such a centrifugal compressor.
- turbomachinery is understood to mean machines such as, for example, single or double flow turbojets, turboprops, turboshaft engines and / or turbochargers.
- upstream and downstream are defined with respect to the normal flow direction of fluid through the compressor.
- front, rear, axial and radial are defined relative to the axis of rotation of the impeller.
- a centrifugal compressor normally comprises a fixed part and a rotating part called wheel and comprising the rotating blades of the compressor.
- the impeller In operation, the impeller typically rotates at a high speed. It is therefore subject to centrifugal constraints.
- the shape of the impeller of a centrifugal compressor is dictated by the flow of fluid through the compressor.
- the fluid enters the compressor in a substantially axial direction, that is to say, parallel to the axis of rotation of the impeller.
- the vein and the rotating blades direct the fluid radially outward, so that the fluid leaves the wheel in a direction substantially orthogonal to the axis of rotation of the wheel.
- the blades thus have substantially radial leading edges and trailing edges substantially axial, further from the axis of rotation of the wheel in radial direction and located axially behind the leading edges.
- the veil secures the vanes rotating between them and with the compressor shaft.
- each blade is secured to the web and located on a front face of the web.
- the veil also serves to delimit the foot of the flow vein of the fluid through the impeller. It is therefore normally axisymmetric and curved progressively outwards in the axial direction.
- the German patent DE 906 975 proposes a spinning wheel whose sail is more advanced in the axial direction at the periphery than at an intermediate diameter of the impeller.
- this wheel also requires a reinforcing disc fixed on the blade heads, in order to restrict the deformation of the periphery of the impeller in the axial direction, which can be difficult to adapt to an existing compressor or a turbomachine in the aeronautics, in which the restriction of the masses is one of the main priorities.
- the US patent application US 2007/0077147 A1 and the British patent GB 553.747 illustrate other spinning wheels advanced periphery, but are not proposed to solve the problem of axial deformation of the wheel at high speeds.
- a point of intersection of the trailing edge and the blade root is more advanced than the blade root at an intermediate diameter of the wheel. In particular, it may be more advanced by at least half a thickness of sail.
- a point of intersection of the trailing edge and the blade head is also more advanced than the blade head at an intermediate diameter of the impeller. In this way, the bending moment at the periphery of the impeller is reversed, and its maximum absolute value is reduced, which limits the deformations of the impeller in the axial direction, while maintaining a good aerodynamic efficiency.
- the front face is oriented in a substantially radial direction. This provides a rectification of the fluid flow output of the wheel which allows the use of a conventional radial diffuser downstream of the wheel.
- the wheel further comprises a rim connected to a rear face of the veil and adapted to be fixed to the rotary shaft.
- the rim may comprise a radial attachment leek. An efficient and comparatively light attachment of the impeller to the rotary shaft of the compressor can thus be obtained.
- the centrifugal compressor further comprises a cover covering the blades so as to define, with the web, a vein of fluid between the leading edges and the vanishing edges of the blades.
- the aerodynamic losses of the centrifugal compressor can thus be substantially reduced by limiting in this way an overflow of fluid from the intrados to the extrados of each blade.
- the cover may then comprise at least one attachment point closer to the trailing edges of the rotor blades than the leading edges of the rotor blades.
- the axial attachment of the cover can be positioned closer to the periphery of the impeller. , which limits the clearance between the cover and the rotor blades at the periphery of the wheel in partial regimes and thus increase the aerodynamic efficiency.
- the lid may be integral with the blades, so as to form a flanged wheel.
- a turbomachine more specifically in the form of a turbine engine 1, is illustrated schematically for explanatory purposes on the figure 1 .
- This turbine engine 1 comprises, in the direction of flow of a working fluid, an axial compressor 2, a centrifugal compressor 3, a combustion chamber 4, a first axial turbine 5, and a second axial turbine 6.
- the turbine engine 1 also comprises a first rotary shaft 7 and a second rotary shaft 8 coaxial with the first rotary shaft 7.
- the second rotary shaft 8 connects the axial compressor 2 and the centrifugal compressor 3 to the first axial turbine 5, so that the expansion of the working fluid in this first axial turbine 5 downstream of the combustion chamber 4 serves to actuate compressors 2 and 3 upstream of the combustion chamber 4.
- the first rotary shaft 7 connects the second axial turbine 6 to a power output 9 positioned downstream and / or upstream of the machine, so that the subsequent detent working fluid in the second axial turbine 6 downstream of the first axial turbine 5 serves to actuate the power output 9.
- the consecutive compressions of the working fluid in the axial compressors 2 and centrifugal 3, followed by a heating of the working fluid in the combustion chamber 4, and its expansion in the second axial turbine 6 allow the conversion of a part of the thermal energy introduced by combustion into the combustion chamber 4 in mechanical work extracted by the power output 9.
- the driving fluid is air, to which is added and in which a fuel is burned in the combustion chamber 4, fuel such as, for example, a hydrocarbon.
- the rotary shafts 7 and 8 rotate at speeds of the order of 5000 to 60000 revolutions per minute.
- the rotating parts of the compressors 2 and 3 and the turbines 5 and 6 are therefore subjected to great efforts by the centrifugal forces.
- FIG 2 it can be appreciated how these centrifugal forces act on the wheel 101 of a conventional centrifugal compressor known to those skilled in the art.
- This wheel 101 has a sail 102 substantially axisymmetric and having a front face 103 and a rear face 104.
- the blades 105 are fixed by the blade roots 115 on the front face 103 of the sail 102.
- Each blade 105 also has a blade head 116 opposite to the blade root 115, a leading edge 106 with a substantially radial orientation and a trailing edge 107 with a substantially axial orientation, located radially outside and axially behind the leading edge 106.
- the working fluid is thus sucked by the front 108 of the wheel 101 and directed by the blades 105 to the periphery 109 of the impeller 101, following a stream of fluid defined internally by the web 102 and externally by a non-rotating cover 110 of the centrifugal compressor near the blade heads 116.
- the web 102 On its rear face, the web 102 is secured to a rim 111 with a leek for attachment to the rotary shaft.
- the rim 111 and the leek thus define a plane A for transmitting the radial forces of the wheel 101 to the rotary shaft.
- the centrifugal forces exerted on the wheel 101 represent a preponderant part of these radial forces.
- the centrifugal force F c is proportional to the square of the angular rotation speed ⁇ multiplied by the distance to the axis of rotation X of the wheel 101, according to the formula ⁇ 2 r, the centrifugal forces exerted on the periphery 109 of the wheel 101 will be preponderant.
- the centrifugal force F c acting on the periphery 109 of the impeller 101 will create a bending moment M F in the wheel 101 tending to tilt the periphery 109 of the impeller 101 to the front.
- This bending moment M F increases continuously from the periphery 109 of the wheel 101 to the junction of the veil 102 with the rim 111.
- the veil 102, the rim 111 and the leek must be reinforced. which results in a considerable increase in the total mass of the wheel 101.
- the figure 3 shows the centrifugal compressor 3 with a wheel 201 according to a first embodiment of the invention.
- This wheel 201 also comprises a substantially axisymmetric web 202 and having a front face 203 and a rear face 204.
- the blades 205 are fixed by the blade roots 215 on the front face 203 of the web 202 and each also have a blade head 216 opposite to the blade root 215, a leading edge 206 with a substantially radial orientation and a trailing edge 207 with a substantially axial orientation, situated radically outside and axially behind the leading edge 206.
- the compressor 3 comprises a conventional radial diffuser 212 with straightening vanes 213.
- the working fluid is thus also sucked by the front 208 of the impeller 201 and directed by the blades 205 towards the periphery 209 of the impeller 201, according to a fluid stream defined inside by the web 202 and to the outside by the non-rotating cover 210, to arrive at the radial diffuser 212.
- the web 202 On its rear face, the web 202 is also secured to a rim 211 with a leek attachment to the rotary shaft. However, in this wheel 201, the web 202 is curved so that a peripheral segment of the web 202 is inclined forward: from an intermediate diameter D i , thus having a concave front face 203. Thus, at the periphery 209 of the wheel 201, this front face 203 is advanced by a distance L with respect to the intermediate diameter D i . This distance L is substantial, and in particular it is greater than half the thickness d of the web 202 at the periphery 209 of the impeller 201.
- the clearance dp between the tips of the blades 205 at the periphery of the impeller 201 and the cover 210 can also be reduced, and this cover 210 can be fixed in a comparatively rigidly on an attachment point 214 closer to the rear of the cover 210 and thus the trailing edges 207 than the front of the cover 210 and the leading edges 206.
- An additional advantage lies in the reduced axial size of the impeller 201, and in particular in the reduced axial distance between the inlet of the working fluid at the front of the impeller 201 and its output at the periphery 209 of the impeller 201.
- this makes it possible to substantially advance the elements downstream of the compressor, that is to say, in the embodiment illustrated, the hot parts such as the combustion chamber 4, and the first and second axial turbines 5 and 6, to thereby reduce the overall axial dimension of the turbomachine.
- the outer edge of the peripheral segment 202c of the web 202 is curved so as to reorient the front face 203 of the web 202 in the radial direction, and thus straighten the fluid vein in the radial direction to be able to use the conventional radial diffuser 212 illustrated.
- each equivalent element receives the same reference numeral as on the figure 3 the fluid stream is not rectified radially, which facilitates the production of the wheel, even if the diffuser downstream of the wheel must be adapted.
- a centrifugal compressor with a wheel 201 such as those illustrated on the Figures 3 and 4 can be used, inter alia, in turbomachines such as the turbine engine 1 illustrated in FIG. figure 1 but also single or double flow turbojets, turboprops, turboshaft engines and / or turbochargers.
- turbomachines such as the turbine engine 1 illustrated in FIG. figure 1 but also single or double flow turbojets, turboprops, turboshaft engines and / or turbochargers.
- By its reduced mass it will be particularly advantageous in an aeronautical use, such as that, for example, for the propulsion of fixed and / or rotary wing aircraft, with or without a pilot, lighter or heavier than air.
- other non-aeronautical applications known to those skilled in the art may also be envisaged, such as, for example, the propulsion of land and / or marine vehicles, including air cushion vehicles, electrical generation, pumping stations, and / or other industrial applications.
- Such a centrifugal compressor may constitute the only stage of a compression system, or one or more of the stages of a multi-stage compression system, axial, mixed or centrifugal, that is to say comprising at least one centrifugal stage and an axial stage or a mixed stage.
Description
La présente invention concerne le domaine des compresseurs centrifuges.The present invention relates to the field of centrifugal compressors.
L'invention concerne plus particulièrement un rouet de compresseur centrifuge comportant un voile et des aubes solidaires du voile sur une face avant du voile, ayant chacune un bord d'attaque et un bord de fuite, ainsi qu'un compresseur centrifuge comprenant un tel rouet, et une turbomachine comprenant un tel compresseur centrifuge. On entend par turbomachine, dans ce contexte, des machines telles que, par exemple, des turboréacteurs à simple ou double flux, des turbopropulseurs, des turbomoteurs et/ou des turbocompresseurs.The invention more particularly relates to a centrifugal compressor wheel comprising a web and vanes integral with the web on a front face of the web, each having a leading edge and a trailing edge, and a centrifugal compressor comprising such a wheel , and a turbomachine comprising such a centrifugal compressor. In this context, turbomachinery is understood to mean machines such as, for example, single or double flow turbojets, turboprops, turboshaft engines and / or turbochargers.
Dans la description qui suit les termes « amont » et « aval » sont définis par rapport au sens de circulation normal de fluide à travers le compresseur. Les termes « avant », « arrière », « axial et « radial » sont définis par rapport à l'axe de rotation du rouet.In the following description the terms "upstream" and "downstream" are defined with respect to the normal flow direction of fluid through the compressor. The terms "front", "rear", "axial" and "radial" are defined relative to the axis of rotation of the impeller.
Un compresseur centrifuge comporte normalement une partie fixe et une partie tournante dénommée rouet et comprenant les aubes tournantes du compresseur. En fonctionnement, le rouet tourne typiquement à une vitesse élevée. Il est donc soumis à des contraintes d'ordre centrifuge.A centrifugal compressor normally comprises a fixed part and a rotating part called wheel and comprising the rotating blades of the compressor. In operation, the impeller typically rotates at a high speed. It is therefore subject to centrifugal constraints.
La forme du rouet d'un compresseur centrifuge est dictée par l'écoulement du fluide à travers le compresseur. Typiquement, dans un tel compresseur centrifuge, le fluide entre dans le compresseur dans une direction sensiblement axiale, c'est-à-dire, parallèle à l'axe de rotation du rouet. La veine et les aubes tournantes dirigent le fluide radialement vers l'extérieur, de telle manière que le fluide quitte le rouet dans une direction sensiblement orthogonale à l'axe de rotation du rouet. Les aubes ont donc des bords d'attaque sensiblement radiaux et des bords de fuite sensiblement axiaux, plus éloignés de l'axe de rotation du rouet en direction radiale et situés axialement derrière les bords d'attaque.The shape of the impeller of a centrifugal compressor is dictated by the flow of fluid through the compressor. Typically, in such a centrifugal compressor, the fluid enters the compressor in a substantially axial direction, that is to say, parallel to the axis of rotation of the impeller. The vein and the rotating blades direct the fluid radially outward, so that the fluid leaves the wheel in a direction substantially orthogonal to the axis of rotation of the wheel. The blades thus have substantially radial leading edges and trailing edges substantially axial, further from the axis of rotation of the wheel in radial direction and located axially behind the leading edges.
Le voile solidarise les aubes tournantes entre elles et avec l'arbre du compresseur. Pour cela chacune des aubes est solidaire du voile et située sur une face avant de ce voile. Le voile sert aussi à délimiter le pied de la veine d'écoulement du fluide à travers le rouet. Il est donc normalement axisymétrique et incurvé progressivement vers l'extérieur dans la direction axiale. Par cette forme du voile et des aubes, l'accélération centrifuge génère un couple de flexion sur le rouet tendant à fléchir la périphérie du rouet vers l'avant. Ce couple de flexion s'accroît de manière continue de la périphérie du rouet vers la connexion du voile à l'arbre du compresseur, et oblige à maintenir des jeux importants à régime partiel pénalisant les performances de la machine. Afin de résister à ce couple, il a été typiquement proposé de renforcer le voile et les moyens de fixation du rouet à l'arbre rotatif. Toutefois, renforcer d'une telle manière les parties tournantes d'un rouet de compresseur impose une pénalité en masse très importante, car la masse qui sera ajoutée à proximité de la veine d'air nécessitera par ailleurs un grossissement de l'alésage du rouet.The veil secures the vanes rotating between them and with the compressor shaft. For this, each blade is secured to the web and located on a front face of the web. The veil also serves to delimit the foot of the flow vein of the fluid through the impeller. It is therefore normally axisymmetric and curved progressively outwards in the axial direction. By this shape of the web and the blades, the centrifugal acceleration generates a bending moment on the wheel tending to bend the periphery of the wheel forward. This bending moment increases continuously from the periphery of the wheel to the connection of the sail to the compressor shaft, and forces to maintain significant games at partial speed penalizing the performance of the machine. In order to resist this torque, it has been typically proposed to reinforce the web and the fixing means of the wheel to the rotary shaft. However, to strengthen in such a way the rotating parts of a compressor wheel imposes a very large mass penalty, because the mass that will be added near the air stream will also require a magnification of the wheel bore .
Afin d'éviter cet inconvénient, il a été proposé, dans le brevet
Dans la demande de brevet britannique
Le brevet allemand
La présente invention vise à remédier à ces inconvénients. Selon un premier aspect, un point d'intersection du bord de fuite et du pied d'aube est plus avancé que le pied d'aube à un diamètre intermédiaire du rouet. En particulier, il peut être plus avancé d'au moins une demi-épaisseur de voile. En outre, un point d'intersection du bord de fuite et de la tête d'aube est aussi plus avancé que la tête d'aube à un diamètre intermédiaire du rouet. De cette manière, le couple de flexion en périphérie du rouet est inversé, et sa valeur absolue maximale est réduite, ce qui limite les déformations du rouet en direction axiale, tout en maintenant un bon rendement aérodynamique.The present invention aims to remedy these disadvantages. In a first aspect, a point of intersection of the trailing edge and the blade root is more advanced than the blade root at an intermediate diameter of the wheel. In particular, it may be more advanced by at least half a thickness of sail. In addition, a point of intersection of the trailing edge and the blade head is also more advanced than the blade head at an intermediate diameter of the impeller. In this way, the bending moment at the periphery of the impeller is reversed, and its maximum absolute value is reduced, which limits the deformations of the impeller in the axial direction, while maintaining a good aerodynamic efficiency.
Selon un deuxième aspect, en périphérie du rouet, la face avant est orientée en direction sensiblement radiale. On obtient ainsi un redressement de l'écoulement du fluide en sortie du rouet qui permet l'utilisation d'un diffuseur radial classique en aval du rouet.According to a second aspect, at the periphery of the wheel, the front face is oriented in a substantially radial direction. This provides a rectification of the fluid flow output of the wheel which allows the use of a conventional radial diffuser downstream of the wheel.
Selon un troisième aspect, le rouet comporte en outre une jante reliée à une face arrière du voile et apte à être fixée à l'arbre rotatif. En particulier, la jante peut comprendre un poireau de fixation radiale. Une fixation efficace et comparativement légère du rouet à l'arbre rotatif du compresseur peut ainsi être obtenue.According to a third aspect, the wheel further comprises a rim connected to a rear face of the veil and adapted to be fixed to the rotary shaft. In particular, the rim may comprise a radial attachment leek. An efficient and comparatively light attachment of the impeller to the rotary shaft of the compressor can thus be obtained.
Selon un quatrième aspect, le compresseur centrifuge comporte en outre un couvercle recouvrant les aubes de manière à délimiter, avec le voile, une veine de fluide entre les bords d'attaque el les bords de fuite des aubes. Les pertes aérodynamiques du compresseur centrifuge peuvent ainsi être sensiblement réduites en limitant de cette manière un débordement de fluide de l'intrados à l'extrados de chaque aube. En particulier le couvercle peut alors comporter au moins un point de fixation plus proche des bords de fuite des aubes du rouet que des bords d'attaque des aubes du rouet. Comme le déplacement axial de la périphérie radiale du rouet à haut régime peut être limité par la non-bijectivité en direction axiale de la courbe formée par la face avant du voile, la fixation axiale du couvercle peut être positionnée plus proche de la périphérie du rouet, ce qui permet de limiter le jeu entre le couvercle et les aubes du rouet en périphérie du rouet dans des régimes partiels et ainsi augmenter le rendement aérodynamique. Alternativement, le couvercle peut être solidaire des aubes, de manière à former un rouet flasqué.According to a fourth aspect, the centrifugal compressor further comprises a cover covering the blades so as to define, with the web, a vein of fluid between the leading edges and the vanishing edges of the blades. The aerodynamic losses of the centrifugal compressor can thus be substantially reduced by limiting in this way an overflow of fluid from the intrados to the extrados of each blade. In particular the cover may then comprise at least one attachment point closer to the trailing edges of the rotor blades than the leading edges of the rotor blades. Since the axial displacement of the radial periphery of the impeller at high speed can be limited by the non-bijectivity in the axial direction of the curve formed by the front face of the web, the axial attachment of the cover can be positioned closer to the periphery of the impeller. , which limits the clearance between the cover and the rotor blades at the periphery of the wheel in partial regimes and thus increase the aerodynamic efficiency. Alternatively, the lid may be integral with the blades, so as to form a flanged wheel.
L'invention sera bien comprise et ses avantages apparaîtront mieux, à la lecture de la description détaillée qui suit, de modes de réalisation représentés à titre d'exemples non limitatifs. La description se réfère aux dessins annexés sur lesquels :
- la
figure 1 est une coupe longitudinale schématique d'une turbomachine comportant un compresseur centrifuge ; - la
figure 2 est une coupe longitudinale d'un rouet de compresseur centrifuge de l'art antérieur ; - la
figure 3 est une coupe longitudinale d'un compresseur centrifuge suivant un premier mode de réalisation de l'invention ; - la
figure 4 est une coupe longitudinale d'un rouet de compresseur centrifuge suivant un deuxième mode de réalisation de l'invention.
- the
figure 1 is a schematic longitudinal section of a turbomachine comprising a centrifugal compressor; - the
figure 2 is a longitudinal section of a centrifugal compressor wheel of the prior art; - the
figure 3 is a longitudinal section of a centrifugal compressor according to a first embodiment of the invention; - the
figure 4 is a longitudinal section of a centrifugal compressor impeller according to a second embodiment of the invention.
Une turbomachine, plus spécifiquement sous forme d'un turbomoteur 1, est illustrée schématiquement à titre explicatif sur la
Le deuxième arbre rotatif 8 relie le compresseur axial 2 et le compresseur centrifuge 3 à la première turbine axiale 5, de manière à ce que la détente du fluide de travail dans cette première turbine axiale 5 en aval de la chambre de combustion 4 serve à actionner les compresseurs 2 et 3 en amont de la chambre de combustion 4. Le premier arbre rotatif 7 relie la deuxième turbine axiale 6 à une sortie de puissance 9 positionnée en aval et/ou en amont de la machine, de telle manière que la détente subséquente du fluide de travail dans la deuxième turbine axiale 6 en aval de la première turbine axiale 5 serve à actionner la sortie de puissance 9.The second
Ainsi, les compressions consécutives du fluide de travail dans les compresseurs axial 2 et centrifuge 3, suivies par un réchauffement du fluide de travail dans la chambre de combustion 4, et sa détente dans la deuxième turbine axiale 6 permettent la conversion d'une partie de l'énergie thermique introduite par la combustion dans la chambre de combustion 4 en travail mécanique extrait par la sortie de puissance 9. Dans la turbomachine illustrée, le fluide moteur est de l'air, auquel on ajoute et dans lequel on brûle un carburant dans la chambre de combustion 4, carburant tel que, par exemple, un hydrocarbure.Thus, the consecutive compressions of the working fluid in the
En fonctionnement, les arbres rotatifs 7 et 8 tournent à des vitesses de l'ordre de 5000 à 60000 tours par minute. Les parties tournantes des compresseurs 2 et 3 et des turbines 5 et 6 sont donc soumises à des efforts importants par les forces centrifuges. Tournant désormais vers la
Sur sa face arrière, le voile 102 est solidaire d'une jante 111 avec un poireau de fixation à l'arbre rotatif. La jante 111 et le poireau définissent donc un plan A de transmission des efforts radiaux du rouet 101 à l'arbre rotatif. A cause des hautes vitesses de rotation du rouet 101, les forces centrifuges exercées sur le rouet 101 représentent une partie prépondérante de ces efforts radiaux. Toutefois, comme la force centrifuge Fc est proportionnelle au carré de la vitesse angulaire de rotation ω multiplié par la distance à l'axe de rotation X du rouet 101, suivant la formule ω2r, les forces centrifuges exercées sur la périphérie 109 du rouet 101 vont être prépondérantes. Ainsi, dans le rouet 101 classique illustré, les forces centrifuges Fc agissant sur la périphérie 109 du rouet 101 créeront un couple de flexion MF dans le rouet 101 tendant à basculer la périphérie 109 du rouet 101 vers l'avant. Ce couple de flexion MF augmente continuellement de la périphérie 109 du rouet 101 à la jonction du voile 102 avec la jante 111. Afin de limiter la flexion du rouet 101, le voile 102, la jante 111 et le poireau doivent être renforcés, ce qui se traduit par une augmentation considérable de la masse totale du rouet 101. En outre, pour accommoder le déplacement vers l'avant de la périphérie 109 du rouet 101, il est normalement nécessaire d'accorder en périphérie du rouet 101 un jeu important dp à régime partiel entre les têtes d'aube 105b et le couvercle 110, ce qui se traduit par des pertes aérodynamiques importantes, ou même d'arranger des structures de fixation du couvercle 110 assez complexes, afin d'induire un déplacement du couvercle 110 vers l'avant: lors d'une montée en régime du compresseur.On its rear face, the
La
Sur sa face arrière, le voile 202 est aussi solidaire d'une jante 211 avec un poireau de fixation à l'arbre rotatif. Toutefois, dans ce rouet 201, le voile 202 est incurvé de manière à ce qu'un segment périphérique du voile 202 soit incliné vers l'avant: à partir d'un diamètre intermédiaire Di, présentant ainsi une face avant 203 concave. Ainsi, en périphérie 209 du rouet 201, cette face avant 203 est avancée d'une distance L par rapport au diamètre intermédiaire Di. Cette distance L est substantielle, et en particulier elle est supérieure à la moitié de l'épaisseur d du voile 202 en périphérie 209 du rouet 201. En conséquence, sur un segment périphérique 202c tourné vers l'avant, les efforts centrifuges Fc génèrent un couple de flexion MF tendant à fléchir ce segment périphérique 202c, non pas vers l'avant, mais en sens opposé, vers l'arrière. Le module de ce couple de flexion MF augmente à partir de la périphérie 209 jusqu'au diamètre intermédiaire Di, où il atteint un maximum local. Ensuite, il diminue toutefois jusqu'à ce éventuellement inverser le sens du couple de flexion MF. Ainsi, comme le couple de flexion MF n'augmente pas continuellement de la périphérie 209 à la jonction du voile 202 avec la jante 211, il atteint des niveaux sensiblement moindres que dans le rouet 101 de l'état de la technique, permettant ainsi l'utilisation d'une jante 211 et un poireau de fixation plus légers. En outre, comme le déplacement axial de la périphérie 209 du rouet 201 est réduit, le jeu dp entre le sommet des aubes 205 en périphérie du rouet 201 et le couvercle 210 peut aussi être réduit, et ce couvercle 210 peut être fixé de manière comparativement rigide sur un point de fixation 214 plus proche de l'arrière du couvercle 210 et donc des bords de fuite 207 que de l'avant du couvercle 210 et les bords d'attaque 206.On its rear face, the
Un avantage additionnel réside dans l'encombrement axial réduit du rouet 201, et en particulier dans la distance axiale réduite entre l'entrée du fluide de travail au front du rouet 201 et sa sortie en périphérie 209 du rouet 201. En particulier dans une turbomachine telle que le turbomoteur 1 illustré sur la
Dans le mode de réalisation illustré sur la
Un compresseur centrifuge avec un rouet 201 tel que ceux illustrés sur les
Quoique la présente invention ait été décrite en se référant à des exemples de réalisation spécifiques, il est évident que des différentes modifications et changements peuvent être effectués sur ces exemples sans sortir de la portée générale de l'invention telle que définie par les revendications. En particulier, des caractéristiques individuelles des différents modes de réalisation illustrés peuvent être combinées dans des modes de réalisation additionnells. Par conséquent, la description et les dessins doivent être considérés dans un sens illustratif plutôt que restrictif.Although the present invention has been described with reference to specific exemplary embodiments, it is obvious that various modifications and changes can be made to these examples without departing from the general scope of the invention as defined by the claims. In particular, individual features of the various illustrated embodiments may be combined in additional embodiments. Therefore, the description and drawings should be considered in an illustrative rather than restrictive sense.
Claims (9)
- An impeller (201) for a centrifugal compressor (3), the impeller comprising a web (202) and blades (205) secured to the web (202) on a front face (203) of the web (202), each having a blade root (215), a blade tip (216), a leading edge (206), and a trailing edge (207), the impeller (201) being characterized in that a point of intersection between the trailing edge (207) and the blade root (215) is further forward by at least one half-thickness of the web (202) than is the blade root (215) at an intermediate diameter (Di) of the impeller (201), and a point of intersection between the trailing edge (207) and the blade tip (216) is also further forward than the blade tip (216) at an intermediate diameter (Di) of the impeller (201).
- An impeller (201) for a centrifugal compressor (3) according to claim 1, wherein the blade root (215) at a periphery (209) of the impeller (201) is oriented in a direction that is substantially radial.
- An impeller (201) for a centrifugal compressor (3) according to claim 1 or claim 2, further including a rim (211) connected to a rear face (204) of the web (202) and suitable for being fastened to a rotary shaft.
- An impeller (201) for a centrifugal compressor (3) according to claim 3, wherein the rim (211) includes a radial fastener disk.
- A centrifugal compressor (3) including an impeller (201) according to any one of claims 1 to 4.
- A centrifugal compressor (3) according to claim 5, further including a cover (210) covering the blades (205) so as to co-operate with the web (202) to define a fluid flow passage between the leading edges (206) and the trailing edges (207) of the blades (205).
- A centrifugal compressor (3) according to claim 6, wherein the cover (210) includes at least one fastener point (214) closer to the trailing edges (207) of the blades (205) of the impeller (201) than to the leading edges (206) of the blades (205) of the impeller (201).
- A centrifugal compressor (3) according to claim 6, wherein the cover is secured to the blades (205).
- A turbine engine including a centrifugal compressor (3) according to any one of claims 5 to 8.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PL12728683T PL2715146T3 (en) | 2011-05-23 | 2012-05-14 | Centrifugal compressor impeller |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1154461A FR2975733B1 (en) | 2011-05-23 | 2011-05-23 | CENTRIFUGAL COMPRESSOR WHEEL |
PCT/FR2012/051074 WO2012160290A1 (en) | 2011-05-23 | 2012-05-14 | Centrifugal compressor impeller |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2715146A1 EP2715146A1 (en) | 2014-04-09 |
EP2715146B1 true EP2715146B1 (en) | 2016-04-20 |
Family
ID=46321108
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP12728683.9A Active EP2715146B1 (en) | 2011-05-23 | 2012-05-14 | Centrifugal compressor impeller |
Country Status (11)
Country | Link |
---|---|
US (1) | US9683576B2 (en) |
EP (1) | EP2715146B1 (en) |
JP (1) | JP6009546B2 (en) |
KR (1) | KR101891853B1 (en) |
CN (1) | CN103562557B (en) |
CA (1) | CA2836040C (en) |
ES (1) | ES2573335T3 (en) |
FR (1) | FR2975733B1 (en) |
PL (1) | PL2715146T3 (en) |
RU (1) | RU2583322C2 (en) |
WO (1) | WO2012160290A1 (en) |
Families Citing this family (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2014214649A (en) * | 2013-04-24 | 2014-11-17 | トヨタ自動車株式会社 | Multistage compressor |
JP2014234729A (en) * | 2013-05-31 | 2014-12-15 | 株式会社Ihi | Centrifugal compressor and gas turbine engine |
FR3007086B1 (en) * | 2013-06-18 | 2015-07-03 | Cryostar Sas | CENTRIFUGAL WHEEL |
FR3018114B1 (en) | 2014-03-03 | 2016-03-25 | Turbomeca | DEVICE FOR POSITIONING AN INSPECTION TOOL |
JP2016061223A (en) * | 2014-09-18 | 2016-04-25 | 株式会社Ihi | Turbo rotary machine |
US9970452B2 (en) * | 2015-02-17 | 2018-05-15 | Honeywell International Inc. | Forward-swept impellers and gas turbine engines employing the same |
CN110985436A (en) * | 2019-12-24 | 2020-04-10 | 苏州苏磁智能科技有限公司 | Fluid force balance structure of high-speed centrifugal impeller |
US11795821B1 (en) * | 2022-04-08 | 2023-10-24 | Pratt & Whitney Canada Corp. | Rotor having crack mitigator |
Family Cites Families (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1447916A (en) * | 1920-12-18 | 1923-03-06 | American Blower Co | Centrifugal fan |
GB553747A (en) * | 1940-12-17 | 1943-06-03 | Johann Fullemann | Improvements in and relating to impellers for blowers |
US2543923A (en) * | 1948-04-13 | 1951-03-06 | Ward T Mixsell | Radial air compressor |
DE906975C (en) * | 1950-05-03 | 1954-03-18 | Licentia Gmbh | Impeller for radial turbo compressors |
US3365892A (en) * | 1965-08-10 | 1968-01-30 | Derderian George | Turbomachine |
SU367286A1 (en) * | 1971-05-21 | 1973-01-23 | TEMPERATURE OPERATING WHEEL | |
FR2230229A5 (en) * | 1973-05-16 | 1974-12-13 | Onera (Off Nat Aerospatiale) | |
US4060337A (en) | 1976-10-01 | 1977-11-29 | General Motors Corporation | Centrifugal compressor with a splitter shroud in flow path |
SU769104A1 (en) * | 1977-12-12 | 1980-10-07 | Казанский Химико-Технологический Институт Им.С.М.Кирова | Centrifugal pump impeller |
JPS57112100U (en) * | 1980-12-27 | 1982-07-10 | ||
US5020971A (en) * | 1985-01-08 | 1991-06-04 | Super Stream, Inc. | Rotatable assembly |
JP2004353607A (en) * | 2003-05-30 | 2004-12-16 | Mitsubishi Heavy Ind Ltd | Centrifugal compressor |
JP4209362B2 (en) * | 2004-06-29 | 2009-01-14 | 三菱重工業株式会社 | Centrifugal compressor |
US20060263214A1 (en) | 2005-05-19 | 2006-11-23 | Matheny Alfred P | Centrifugal impeller with forward and reverse flow paths |
US7476081B2 (en) * | 2005-10-03 | 2009-01-13 | Mitsubishi Heavy Industries, Ltd. | Centrifugal compressing apparatus |
EP2090788A1 (en) | 2008-02-14 | 2009-08-19 | Napier Turbochargers Limited | Impeller and turbocharger |
US8241005B2 (en) | 2008-10-16 | 2012-08-14 | Rolls-Royce North American Technologies, Inc. | Gas turbine engine centrifugal impeller |
GB2472621A (en) | 2009-08-13 | 2011-02-16 | Rolls Royce Plc | Impeller hub |
CN101922459B (en) * | 2010-07-28 | 2012-06-13 | 康跃科技股份有限公司 | Electric composite multi-stage centrifugal compressor device |
-
2011
- 2011-05-23 FR FR1154461A patent/FR2975733B1/en active Active
-
2012
- 2012-05-14 JP JP2014511930A patent/JP6009546B2/en not_active Expired - Fee Related
- 2012-05-14 CA CA2836040A patent/CA2836040C/en not_active Expired - Fee Related
- 2012-05-14 RU RU2013156810/06A patent/RU2583322C2/en active
- 2012-05-14 PL PL12728683T patent/PL2715146T3/en unknown
- 2012-05-14 US US14/119,454 patent/US9683576B2/en active Active
- 2012-05-14 CN CN201280025532.XA patent/CN103562557B/en active Active
- 2012-05-14 EP EP12728683.9A patent/EP2715146B1/en active Active
- 2012-05-14 KR KR1020137033179A patent/KR101891853B1/en active IP Right Grant
- 2012-05-14 ES ES12728683.9T patent/ES2573335T3/en active Active
- 2012-05-14 WO PCT/FR2012/051074 patent/WO2012160290A1/en active Application Filing
Also Published As
Publication number | Publication date |
---|---|
CA2836040C (en) | 2020-04-07 |
RU2013156810A (en) | 2015-06-27 |
JP2014515451A (en) | 2014-06-30 |
PL2715146T3 (en) | 2016-08-31 |
FR2975733B1 (en) | 2015-12-18 |
CN103562557A (en) | 2014-02-05 |
CN103562557B (en) | 2016-05-04 |
US20140127023A1 (en) | 2014-05-08 |
KR20140061319A (en) | 2014-05-21 |
KR101891853B1 (en) | 2018-09-28 |
ES2573335T3 (en) | 2016-06-07 |
WO2012160290A1 (en) | 2012-11-29 |
CA2836040A1 (en) | 2012-11-29 |
RU2583322C2 (en) | 2016-05-10 |
EP2715146A1 (en) | 2014-04-09 |
JP6009546B2 (en) | 2016-10-19 |
FR2975733A1 (en) | 2012-11-30 |
US9683576B2 (en) | 2017-06-20 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP2715146B1 (en) | Centrifugal compressor impeller | |
EP2834470B1 (en) | Turbomachine rotor blade, corresponding blisk, compressor rotor and fan rotor | |
EP3361055B1 (en) | Assembly of an axial turbomachine and method of controlling circumferential gaps | |
CA2826153C (en) | Blade-platform assembly for subsonic flow | |
EP2895703B1 (en) | Turbomachine comprising a plurality of variable geometry vanes mounted upstream of the fan | |
EP2715071B1 (en) | Variable-pitch nozzle for a radial flow turbine, in particular for a turbine of an auxiliary power source | |
FR3070448B1 (en) | TURBOMACHINE BLOWER RECTIFIER DRAWER, TURBOMACHINE ASSEMBLY COMPRISING SUCH A BLADE AND TURBOMACHINE EQUIPPED WITH SAID DAUTH OR DUDIT TOGETHER | |
EP1980753B1 (en) | Fan vane | |
FR2889861A1 (en) | Gas turbine engine e.g. turbofan aircraft engine, fan blade, has vane presenting front aerodynamic deflection at distal end, from leading edge to trailing edge, and comprising lower and upper surfaces situated opposite to each other | |
FR3093349A1 (en) | Geared gas turbine engine | |
FR3093350A1 (en) | Geared gas turbine engine | |
FR2508542A1 (en) | PERFECTED TURBINE ENGINEERING BEAN AND ROTOR ASSEMBLY COMPRISING SUCH AUBES | |
EP2805029A1 (en) | Bearing bracket for a turbine engine | |
US10408068B2 (en) | Fan blade dovetail and spacer | |
FR3100579A1 (en) | GAS TURBINE ENGINE | |
FR3096407A1 (en) | Gas 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 | |
EP0349051A1 (en) | Mixed flow compressor and its uses | |
FR3118792A1 (en) | MODULE FOR AN AIRCRAFT TURBOMACHINE | |
FR3089259A1 (en) | Reduction turbofan | |
FR3096408A1 (en) | Gas turbine engine | |
WO2017187093A1 (en) | Air flow rectification assembly and turbomachine comprising an assembly of this type | |
FR2989415A1 (en) | Blade e.g. rotor blade for axial turbofan of e.g. turbojet, has adjacent segment including blade root or blade head, where maximum thickness ratio on cord in segment is greater than maximum thickness ratio on cord in nonadjacent segment |
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: 20131223 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
DAX | Request for extension of the european patent (deleted) | ||
RIN1 | Information on inventor provided before grant (corrected) |
Inventor name: HERRAN, MATHIEU Inventor name: TARNOWSKI, LAURENT, PIERRE |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
INTG | Intention to grant announced |
Effective date: 20160104 |
|
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: 792771 Country of ref document: AT Kind code of ref document: T Effective date: 20160515 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 5 |
|
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: 602012017332 Country of ref document: DE |
|
REG | Reference to a national code |
Ref country code: ES Ref legal event code: FG2A Ref document number: 2573335 Country of ref document: ES Kind code of ref document: T3 Effective date: 20160607 |
|
REG | Reference to a national code |
Ref country code: SE Ref legal event code: TRGR |
|
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: BE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20160531 |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: MK05 Ref document number: 792771 Country of ref document: AT Kind code of ref document: T Effective date: 20160420 |
|
REG | Reference to a national code |
Ref country code: NL Ref legal event code: MP Effective date: 20160420 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
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: 20160720 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: 20160420 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: 20160420 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: 20160420 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: AT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20160420 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: 20160420 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: 20160721 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: 20160420 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: 20160822 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: 20160420 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PL |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R097 Ref document number: 602012017332 Country of ref document: DE |
|
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: 20160531 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: 20160420 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: 20160420 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: 20160420 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: 20160420 Ref country code: CH Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20160531 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: 20160420 |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: MM4A |
|
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: 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: 20160420 |
|
26N | No opposition filed |
Effective date: 20170123 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 6 |
|
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: 20160420 Ref country code: IE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20160514 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: CD Owner name: SAFRAN HELICOPTER ENGINES, FR Effective date: 20170727 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 7 |
|
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: 20120514 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: 20160420 |
|
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: 20160420 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: 20160420 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: 20160420 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: 20160420 Ref country code: LU Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20160514 |
|
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: 20160420 |
|
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: 20160420 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: IT Payment date: 20210422 Year of fee payment: 10 Ref country code: CZ Payment date: 20210426 Year of fee payment: 10 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: SE Payment date: 20210421 Year of fee payment: 10 Ref country code: PL Payment date: 20210426 Year of fee payment: 10 Ref country code: ES Payment date: 20210601 Year of fee payment: 10 |
|
REG | Reference to a national code |
Ref country code: SE Ref legal event code: EUG |
|
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: 20220515 Ref country code: CZ Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20220514 |
|
REG | Reference to a national code |
Ref country code: ES Ref legal event code: FD2A Effective date: 20230726 |
|
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: 20220514 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20230420 Year of fee payment: 12 Ref country code: DE Payment date: 20230419 Year of fee payment: 12 |
|
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: 20220514 |
|
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 NON-PAYMENT OF DUE FEES Effective date: 20220515 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20230420 Year of fee payment: 12 |