EP2558728B1 - Method for adapting the air flow of a turbine engine having a centrifugal compressor and diffuser for implementing same - Google Patents
Method for adapting the air flow of a turbine engine having a centrifugal compressor and diffuser for implementing same Download PDFInfo
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- EP2558728B1 EP2558728B1 EP11730371.9A EP11730371A EP2558728B1 EP 2558728 B1 EP2558728 B1 EP 2558728B1 EP 11730371 A EP11730371 A EP 11730371A EP 2558728 B1 EP2558728 B1 EP 2558728B1
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- blades
- blade
- diffuser
- rotation
- variable pitch
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Images
Classifications
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- 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
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- 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
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- 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
- F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
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- 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
- F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
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- 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 to a method of adapting the air flow rate of a turbomachine comprising a centrifugal compressor, in particular from helicopter turbine engine or auxiliary power unit (abbreviated as APU) to a variable demand for flow rate or mechanical or electrical power.
- APU auxiliary power unit
- the invention also relates to a diffuser equipped with variable pitch blades capable of implementing this method.
- the field of the invention is the compression of gases in turbomachinery engines and, more particularly, the adaptation of the compressed air flow to respect the performance of the engines, be they turboshaft engines or APUs, in particular its consumption. specific (abbreviated Cs) partial load.
- a general problem is to meet the pumping margin requirements and to compensate for compression rate reductions at the intermediate turbine engine speeds, as well as variations in the demand for compressed air flow and electrical power in the engine. case of APU.
- IGV inlet guide vanes
- variable setting is achieved by appropriate controls in connection with a control unit according to the physical parameters involved (rotation speed, pressures, temperatures).
- the ranges of wedges that the control system must cover require a control cylinder of high power, cause significant variations in the inlet and outlet diameters of the diffuser, which can generate high mechanical stresses between rotating parts (wheel) and static (radial variable valve) and decreases the efficiency at partial load (intermediate regime).
- the invention aims to overcome these disadvantages, in particular by maintaining the efficiency of the compressor to substantially reduce the Cs while ensuring a sufficient pumping margin with a better efficiency of the partial load engine cycle. To do this, it proposes an optimized method of variable diffusion of the air flow in a centrifugal compressor of turbomachines.
- the subject of the invention is a method for diffusing variable air flows in a centrifugal compressor of turbomachine engines, consisting in providing a diffusion of air through a first annular grid of variable-pitch blades radially flanged. a second annular grid of same number of fixed-pitch blades of equivalent extension, directing the diffusion in the radial direction by coupling the blades of the two blades, each blade of the first blade being rotated away from the blade.
- Turbomachines should be understood to mean turboshaft engines, in particular helicopter turboshaft engines with a single-stage or two-stage centrifugal compressor, and APUs equipped with a centrifugal compressor of single or two-stage power.
- the radial extension of the variable pitch blades is substantially reduced by the presence of the fixed blade comprising true blades, which limits the efforts to vary their rigging and games between the moving blade and the support flange and thus upstream / downstream recirculation, which has the effect of reducing the deterioration of the pumping line and the pressure drops.
- the decentralized implantation of the axis of rotation of the variable-pitch blades substantially reduces the variations in radial extension of these iso-diffusion blades: the increase in closing is less, thus favoring the efficiency, partial load and decreasing opening less also, which limits the mechanical stresses due to unsteady aerodynamic fluctuations by wheel / diffuser interaction.
- a sufficient pumping margin then allows the turbomachine to operate without pumping - offering a large acceleration capacity -, and the APU to cope with significant load variations, without using a discharge valve, while maintaining the speed of rotation of the turbomachine and its pressure rate to levels close to their nominal values and providing a sufficient level of efficiency.
- the method applying to turbomachines equipped with a power turbine, the variable-displacement radial diffusion on a centrifugal compressor, as defined above, is coupled to a variable-pitch power turbine distributor.
- Power production can be carried out according to several configurations: free power turbine - or linked, of axial or centripetal type, with or without downstream heat exchange.
- the coupling between the diffuser and the variable valve distributor makes it possible to adapt the operating line to the flow reduction, which improves the efficiency of the engine cycle (by a better pressure ratio) and therefore the Cs of the helicopter turboshaft engines. and APUs.
- the subject of the invention is also a variable-speed turbine engine diffuser capable of implementing the method defined above, as well as the turbomachine equipped with such a diffuser.
- the diffuser comprises a first annular grid of variable pitch blades radially bordered by a second annular grid of fixed pitch blades of equivalent extension, forming successive diffusion channels by coupling the blades of the two grids in radial extension.
- each blade of the first gate is driven by control means capable of exerting a proper rotation of each blade off-center with respect to its axis of rotation.
- upstream and downstream refer to the flow direction of the air flow in a turbine engine.
- the centrifugal compressor 10 of a turbomachine such as a turbine engine, turbojet engine, turboprop engine or an APU, comprises a casing 12 coupled to a radial cover 14 of the wheel 16, the centrifugal last stage of the compressor, rotatably mounted on the motor shaft 18 along the axis Y'Y.
- the air flow F flows from the impeller 16 to the annular diffuser 19, in a converging inlet vein by radial shrinkage.
- the diffuser 19 is defined between two upstream and downstream flanges 20 and 22.
- the cover 14 is held by a fastener 23 fixed to the casing and to the upstream flange 20.
- the blades 24, forming a first annular grid, are mounted in the diffuser 19.
- Centerings 25 and 26, formed opposite in the flanges 20 and 22, accommodate the cups 17 and 27 on which the blades 24 are mounted off-center.
- the cups are centered in the flanges 20 and 22 with appropriate clearances, from 0.03 to 0.05 mm in the example illustrated, on a washer 9 inserted in the centering 25 (see below with reference to FIG. figure 5 ).
- Blades 28 secured to the flange 22, forming a second annular grid bordering the outside of the first grid, are mounted on the annular flange 20 by through screws 29 housed in holes 29t. These screws also allow the passage of structural forces.
- the control of the variable blades 24 is achieved by means of rods 30 integrally extending the upstream cup 17.
- rods 30 of X'X axis are mounted in a cylindrical bore 32 of the upstream flange 20 and centered with a virtually zero clearance by joints 30j mounted in grooves 30g.
- each rod 30 has a flat portion 31 articulated on a drive lever 33 clamped by two screws 35 on this flat portion 31.
- the positions of the ends 31 of the rods 30 are adjusted with appropriate play tolerances.
- the rod 30 also has a hole 30t in which a pin 36 is inserted which makes it possible to lock a washer 30u - for adjusting the axial position of the cups 17 and 27 - in a locking ring 12a formed in the casing 12.
- the pin 36 secures the rod 30 and the locking ring 12a.
- the lever 33 is driven by a control ring 34 forming a cylindrical hole 38 for housing the spherical ball 37 of the lever 33 with an adapted axial position tolerance and a contact on a generatrix of the ball joint.
- the control ring 34 is centered on sectors having needle bearings 39.
- the control ring 34 rotated about the motor axis Y'Y by a rod (not shown), rotates the levers 33 which slide in the cylindrical housing 38 thanks to their ball joint 37.
- the depth of the housing 38 is a function of the stroke of the levers 33, itself a function of the rotation interval of the blades 24.
- This architecture is particularly suitable for a rotation of the blades up to + 12 ° with a closing of 50% of section, and up to -5 ° with an opening of section of 20%.
- a movable blade 24 is shown between the parallel cups 17, 27 and joined by welding 21 to them, so that the blade extends parallel to the axis X'X cups facing.
- the leading edge 24c of the blade 24 is flush with the outer circumferences 17c and 27c of the cups, the thickness of the blade 24 being relatively thin, 2 mm in the illustrated example.
- the distance between the blade 24 and the axis X'X of the rod 30 is equal to about 80% of the radius of the cups in the illustrated example. This confers on the blade 24 a strong off-centering with respect to the axis X'X of the rod which coincides with the axis of rotation of the assembly.
- the rod 30 also has the cylindrical centering grooves 30g and the locking hole 30t of the adjusting washer of the axial position of the cups 17 and 27. Its flat portion 31 is traversed by holes 30a for receiving the mounting screws 35. to the control lever.
- the overall view of the figure 3 illustrates the upstream annular flange 20 equipped with annular gates G1 and G2, mounted respectively mobile and fixed and composed of blades 24 and 28.
- the blades 28 have a substantially thicker profile at the leading edge Ba than that of the blades 24, respectively 0.5 and 2.5 mm, in order to preserve good resistance to variations in incidence during the rotation of the movable blades 24.
- the law of skeleton angle of the blades 28 between the leading edges BA and Leakage BF is scalable, making it possible to optimize the aerodynamic efficiency of the fixed gate by a maximum recovery of static pressure.
- the blades 28 of the fixed gate have a maximum thickness of 7 mm in the example shown, for fixing the flange 20 of the diffuser by screws housed in the holes 29t, while allowing the passage of structural forces .
- the air flow F circulates along a fixed blade 28 in radial extension of a movable blade 24 and between two adjacent blades of the same nature, mobile or fixed. Thanks to the off-centering of the mobile blades 24 with respect to the axes of rotation X'X of their cups 17, the variations of the radial extensions formed by these movable blades 24 are limited compared to variations of extensions that should be made of centered blades. This limitation makes it possible to improve the performance of a centrifugal compressor: it makes it possible to move the operating line away from the pumping line, by shifting towards lower flow rates, and to raise this operating line close to the yield maxima. higher diets.
- the radial extensions of the mobile blades 24 with respect to the fixed blades 28 are illustrated by the diagrams of the Figures 4a to 4c , on which also appear, in dotted lines, the cups 17, 27 of the blades.
- the nominal setting of 0 ° corresponds to a flow of the reference air flow F for which the adjustment of the movable blades 24 relative to the fixed blades 28 is adapted to stable intermediate speeds.
- the pitch of the mobile blades 24 can rise up to + 12 °, this wedging corresponding to a passage section at the entrance of the collar Sa, between the blades 24 and 28, closed by 50% relative to at the nominal setting corresponding to a section at the neck Sb.
- the figure 4a illustrates the case of a closure of 25% associated with a wedge of 6 °, the cross-section then being worth 75% of the section Sb.
- the calibration setting can also go down to -5 °.
- the figure 4c illustrates the case of an opening of 2.5 °, the section at the neck Sc then having a relative value of 110%.
- the fixed blades 28 are wedged in azimuth with respect to the blades 24 of the first movable gate G1 so as to resume the wake on the extrados Ex of the blades of this first gate G1.
- the values of the clearances remain less than or equal to 0.02 mm (for J1 or J2), 0.10 mm (for J3) and 0.25 mm (for J4).
- the clearance (set J1 and J2) of the blade 24 on the washer 9 remains about 0.03 mm or slightly higher.
- the invention is not limited to the examples described and shown. It is for example possible to set the pitch of the mobile blades by only mechanical adjustment, individual or centralized, or by electrical, electronic control with or without digital control.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
L'invention concerne un procédé d'adaptation du débit d'air d'une turbomachine comprenant un compresseur centrifuge, en particulier de moteurs de turbomoteur d'hélicoptères ou d'unités de puissance auxiliaires (en abrégé APU) à une demande variable de débit ou de puissance mécanique ou électrique. L'invention se rapporte également à un diffuseur équipé de pales à calage variable apte à mettre en oeuvre ce procédé.The invention relates to a method of adapting the air flow rate of a turbomachine comprising a centrifugal compressor, in particular from helicopter turbine engine or auxiliary power unit (abbreviated as APU) to a variable demand for flow rate or mechanical or electrical power. The invention also relates to a diffuser equipped with variable pitch blades capable of implementing this method.
Le domaine de l'invention est la compression des gaz dans les moteurs de turbomachines et, plus particulièrement, l'adaptation du flux d'air comprimé pour respecter les performances des moteurs, que ce soient des turbomoteurs ou des APU, en particulier sa consommation spécifique (en abrégé Cs) à charge partielle.The field of the invention is the compression of gases in turbomachinery engines and, more particularly, the adaptation of the compressed air flow to respect the performance of the engines, be they turboshaft engines or APUs, in particular its consumption. specific (abbreviated Cs) partial load.
Dans ce contexte, un problème général est de répondre aux besoins de marge au pompage et de pallier aux baisses de taux de compression aux régimes intermédiaires des turbomoteurs, ainsi qu'aux variations de demande de débit d'air comprimé et de puissance électrique dans le cas des APU.In this context, a general problem is to meet the pumping margin requirements and to compensate for compression rate reductions at the intermediate turbine engine speeds, as well as variations in the demand for compressed air flow and electrical power in the engine. case of APU.
Il est connu qu'une marge au pompage suffisante peut être obtenue en abaissant la ligne de fonctionnement des turbomoteurs. Cependant, un abaissement du taux de cycle moteur entraîne une dégradation du rendement et cette solution nécessite alors de faire fonctionner le compresseur en-dessous de son rendement maximum, notamment à haut régime.It is known that a sufficient pumping margin can be obtained by lowering the line of operation of the turboshaft engines. However, a lowering of the engine cycle rate leads to a degradation of the efficiency and this solution then requires operating the compressor below its maximum efficiency, especially at high speed.
Il est également connu d'introduire, à l'entrée du compresseur, une grille de pré-rotation, formée d'ailettes de guidage d'entrée (en abrégé IGV, initiales de « Inlet Guide Vanes » en langue anglaise). Mais, dans ce cas, le taux de compression est sensiblement abaissé pour un régime de rotation donné.It is also known to introduce, at the inlet of the compressor, a pre-rotation grid, formed of inlet guide vanes (abbreviated as IGV, initials of "Inlet Guide Vanes" in English). But in this case, the compression ratio is substantially lowered for a given rotational speed.
Il convient dans ces conditions de chercher à faire fonctionner un compresseur avec un taux de compression quasi constant tout en restant près de son rendement maximum, quelle que soit la variation de la charge.Under these conditions, it is necessary to seek to operate a compressor with a compression ratio almost constant while remaining close to its maximum efficiency, regardless of the variation of the load.
Dans le domaine des compresseurs mono-étages, il existe des diffuseurs radiaux présentant des assemblages de pales à calage variable. De tels diffuseurs sont décrits par exemple dans les documents de brevet
Le calage variable est réalisé par des commandes appropriées en liaison avec une unité de commande en fonction des paramètres physiques en jeu (régime de rotation, pressions, températures). Cependant les plages d'angles de calage que doit couvrir le système de commande nécessitent un vérin de commande d'une puissance élevée, entraînent des variations importantes des diamètres d'entrée et de sortie du diffuseur, ce qui peut générer des sollicitations mécaniques élevées entre parties tournantes (rouet) et statiques (diffuseur radial à calage variable) et diminue le rendement à charge partielle (régime intermédiaire).The variable setting is achieved by appropriate controls in connection with a control unit according to the physical parameters involved (rotation speed, pressures, temperatures). However, the ranges of wedges that the control system must cover require a control cylinder of high power, cause significant variations in the inlet and outlet diameters of the diffuser, which can generate high mechanical stresses between rotating parts (wheel) and static (radial variable valve) and decreases the efficiency at partial load (intermediate regime).
L'invention vise à pallier ces inconvénients, en particulier en maintenant le rendement du compresseur pour diminuer sensiblement la Cs tout en garantissant une marge au pompage suffisante avec un meilleur rendement du cycle moteur à charge partielle. Pour ce faire, elle propose un procédé optimisé de diffusion variable du flux d'air dans un compresseur centrifuge de turbomachines.The invention aims to overcome these disadvantages, in particular by maintaining the efficiency of the compressor to substantially reduce the Cs while ensuring a sufficient pumping margin with a better efficiency of the partial load engine cycle. To do this, it proposes an optimized method of variable diffusion of the air flow in a centrifugal compressor of turbomachines.
Plus précisément, l'invention a pour objet un procédé de diffusion de flux d'air variable dans un compresseur centrifuge de moteurs de turbomachine, consistant à prévoir une diffusion de l'air à travers une première grille annulaire de pales à calage variable bordé radialement d'une deuxième grille annulaire de même nombre de pales à calage fixe d'extension équivalente, orientant la diffusion dans la direction radiale par couplage des pales des deux aubages, chaque pale du premier aubage étant entraînée en rotation à distance de la pale. Par turbomachines, il convient de comprendre les turbomoteurs, en particulier les turbomoteurs d'hélicoptères avec compresseur centrifuge mono-étage ou bi-étages, et les APU équipées de compresseur centrifuge de puissance mono- ou bi-étages.More specifically, the subject of the invention is a method for diffusing variable air flows in a centrifugal compressor of turbomachine engines, consisting in providing a diffusion of air through a first annular grid of variable-pitch blades radially flanged. a second annular grid of same number of fixed-pitch blades of equivalent extension, directing the diffusion in the radial direction by coupling the blades of the two blades, each blade of the first blade being rotated away from the blade. Turbomachines should be understood to mean turboshaft engines, in particular helicopter turboshaft engines with a single-stage or two-stage centrifugal compressor, and APUs equipped with a centrifugal compressor of single or two-stage power.
Dans ces conditions, d'une part, l'extension radiale des pales à calage variable est sensiblement diminuée par la présence de l'aubage fixe comprenant de véritables pales, ce qui permet de limiter les efforts pour faire varier leur calage ainsi que les jeux entre l'aubage mobile et le flasque support et donc les recirculations amont/aval, ce qui a pour effet de diminuer les détériorations de la ligne de pompage et les pertes de charge. D'autre part, l'implantation décentrée de l'axe de rotation des pales à calage variable réduit sensiblement les variations d'extension radiale de ces pales à iso-diffusion : l'augmentation à la fermeture est moindre, favorisant ainsi le rendement, à charge partielle et la diminution à l'ouverture moindre également, ce qui limite les sollicitations mécaniques du fait des fluctuations aérodynamiques instationnaires par interaction rouet / diffuseur.Under these conditions, on the one hand, the radial extension of the variable pitch blades is substantially reduced by the presence of the fixed blade comprising true blades, which limits the efforts to vary their rigging and games between the moving blade and the support flange and thus upstream / downstream recirculation, which has the effect of reducing the deterioration of the pumping line and the pressure drops. On the other hand, the decentralized implantation of the axis of rotation of the variable-pitch blades substantially reduces the variations in radial extension of these iso-diffusion blades: the increase in closing is less, thus favoring the efficiency, partial load and decreasing opening less also, which limits the mechanical stresses due to unsteady aerodynamic fluctuations by wheel / diffuser interaction.
Une marge au pompage suffisante permet alors à la turbomachine de fonctionner sans apparition de pompage - offrant une grande capacité d'accélération -, et à l'APU de faire face à des variations de charge importantes, sans faire appel à une vanne de décharge, tout en maintenant la vitesse de rotation de la turbomachine et son taux de pression à des niveaux proches de leurs valeurs nominales et en fournissant un niveau de rendement suffisant.A sufficient pumping margin then allows the turbomachine to operate without pumping - offering a large acceleration capacity -, and the APU to cope with significant load variations, without using a discharge valve, while maintaining the speed of rotation of the turbomachine and its pressure rate to levels close to their nominal values and providing a sufficient level of efficiency.
Selon des modes particuliers, le procédé s'appliquant à des turbomachines équipées de turbine de puissance, la diffusion radiale à calage variable sur compresseur centrifuge, telle que définie ci-dessus, est couplée à un distributeur de turbine de puissance à calage variable. La production de puissance peut être réalisée selon plusieurs configurations : turbine de puissance libre - ou liée, de type axiale ou centripète, avec ou sans échange thermique aval.According to particular modes, the method applying to turbomachines equipped with a power turbine, the variable-displacement radial diffusion on a centrifugal compressor, as defined above, is coupled to a variable-pitch power turbine distributor. Power production can be carried out according to several configurations: free power turbine - or linked, of axial or centripetal type, with or without downstream heat exchange.
Le couplage entre le diffuseur et le distributeur à calage variable permet d'adapter la ligne de fonctionnement à la diminution de débit, ce qui améliore le rendement du cycle moteur (par un meilleur taux de pression) et donc la Cs des turbomoteurs d'hélicoptères et des APU.The coupling between the diffuser and the variable valve distributor makes it possible to adapt the operating line to the flow reduction, which improves the efficiency of the engine cycle (by a better pressure ratio) and therefore the Cs of the helicopter turboshaft engines. and APUs.
L'invention a également pour objet un diffuseur de turbomachine à calage variable apte à mettre en oeuvre le procédé défini ci-dessus, ainsi que la turbomachine équipée d'un tel diffuseur. Le diffuseur comporte une première grille annulaire de pales à calage variable radialement bordée par une deuxième grille annulaire de pales à calage fixe d'extension équivalente, formant des canaux de diffusion successifs par couplage des pales des deux grilles en extension radiales. De plus, chaque pale de la première grille est entraînée par des moyens de commande aptes à exercer une rotation propre de chaque pale décentrée par rapport à son axe de rotation.The subject of the invention is also a variable-speed turbine engine diffuser capable of implementing the method defined above, as well as the turbomachine equipped with such a diffuser. The diffuser comprises a first annular grid of variable pitch blades radially bordered by a second annular grid of fixed pitch blades of equivalent extension, forming successive diffusion channels by coupling the blades of the two grids in radial extension. In addition, each blade of the first gate is driven by control means capable of exerting a proper rotation of each blade off-center with respect to its axis of rotation.
Selon des modes de réalisation particuliers :
- chaque pale à calage variable s'étend entre deux coupelles en regard et de manière parallèle et décentrée par rapport à l'axe commun des coupelles coïncidant avec l'axe de rotation;
- chaque pale est couplée à une tige d'entraînement qui présente au moins un orifice dans lequel est introduite une goupille de blocage d'une rondelle de réglage de la position axiale des coupelles ;
- la tige est solidarisé à un levier présentant une rotule sphérique logée dans un logement cylindrique (38) d'une couronne de commande apte à entraîner en rotation autour de l'axe moteur le levier apte à coulisser dans le logement cylindrique ;
- les logements cylindriques présente une profondeur qui est fonction de la course des leviers, elle-même fonction de l'intervalle de rotation prédéterminé des pales ;
- le bord d'attaque de chaque pale à calage variable se trouve à proximité des périphéries des coupelles, la distance de la pale à l'axe de rotation étant supérieure ou égale à un demi-rayon ;
- le diffuseur en amont est un diffuseur lisse, c'est-à-dire non aubé ;
- la veine d'air d'entrée du diffuseur située entre le rouet et la grille à calage variable est convergente, ce qui améliore les performances ;
- les pales fixes de la deuxième grille présentent un profil de bord d'attaque plus épais que celles de la première grille afin d'absorber les variations d'incidence;
- les pales à calage fixe présentent une épaisseur suffisante pour être traversées par des vis permettant le passage des efforts structuraux ;
- les pales fixes présentent une loi évolutive d'angle squelette entre les bords d'attaque et de fuite, ce qui permet de contrôler la diffusion dans la grille fixe et d'optimiser son efficacité aérodynamique ;
- les pales fixes sont calées en azimut par rapport aux pales de la première grille mobile de sorte à reprendre le sillage sur l'extrados des pales de cette première grille pour limiter les pertes de charge du diffuseur ;
- les angles de calage des pales variables sont compris entre +12 et - 5 ° par rapport au calage nominal, qui serait celui d'un diffuseur fixe.
- each variable-pitch blade extends between two cups opposite and parallel and off-center with respect to the common axis of the cups coinciding with the axis of rotation;
- each blade is coupled to a drive rod which has at least one orifice in which is introduced a locking pin of a washer for adjusting the axial position of the cups;
- the rod is secured to a lever having a spherical ball received in a cylindrical housing (38) of a control ring adapted to drive in rotation about the motor axis the lever adapted to slide in the cylindrical housing;
- the cylindrical housings have a depth which is a function of the stroke of the levers, itself a function of the predetermined rotation interval of the blades;
- the leading edge of each variable-pitch blade is close to the peripheries of the cups, the distance from the blade to the axis of rotation being greater than or equal to half a radius;
- the diffuser upstream is a smooth diffuser, that is to say, not aubé;
- the air inlet duct of the diffuser located between the impeller and the variable-pitch gate is convergent, which improves the performances;
- the fixed blades of the second grid have a leading edge profile thicker than those of the first grid to absorb the variations of incidence;
- fixed-pitch blades have a thickness sufficient to be traversed by screws allowing the passage of structural forces;
- the fixed blades have an evolutionary law of skeleton angle between the leading and trailing edges, which makes it possible to control the diffusion in the fixed grid and to optimize its aerodynamic efficiency;
- the fixed blades are wedged in azimuth with respect to the blades of the first movable grid so as to resume the wake on the upper surface of the blades of this first gate to limit the pressure losses of the diffuser;
- the angles of setting of the variable blades are between +12 and - 5 ° compared to the nominal setting, which would be that of a fixed diffuser.
D'autres caractéristiques et avantages de l'invention ressortiront à la lecture de la description qui suit, en référence aux figures annexées qui représentent, respectivement :
- la
figure 1 , une demi-vue en coupe axiale partielle d'un diffuseur selon l'invention ; - les
figures 2a et 2b , deux vues en perspective d'une pale à calage variable couplée à sa tige de commande en rotation; - la
figure 3 , une vue globale frontale du flasque annulaire amont du diffuseur équipé des grilles de pales selon l'invention, - les
figures 4a à 4c , une vue schématique partielle dans le diffuseur pour trois calages de pales mobiles, les deux calages extrêmes autour du calage nominal, et - la
figure 5 , les jeux entre une pale mobile et les flasques annulaires du diffuseur.
- the
figure 1 , a half-view in partial axial section of a diffuser according to the invention; - the
Figures 2a and 2b , two perspective views of a variable-pitch blade coupled to its rotating control rod; - the
figure 3 an overall frontal view of the upstream annular flange of the diffuser equipped with the blade grids according to the invention, - the
Figures 4a to 4c , a partial schematic view in the diffuser for three wedges of movable blades, the two extreme wedges around the nominal setting, and - the
figure 5 , the games between a mobile blade and the annular flanges of the diffuser.
Les termes « amont » et « aval » se rapportent au sens d'écoulement du flux d'air dans un turbomoteur.The terms "upstream" and "downstream" refer to the flow direction of the air flow in a turbine engine.
En référence à la vue axiale en coupe partielle de la
Les pales 24, formant une première grille annulaire, sont montées dans le diffuseur 19. Des centrages 25 et 26, formées en regard dans les flasques 20 et 22, accueillent les coupelles 17 et 27 sur lesquelles les pales 24 sont montées de manière décentrée. Les coupelles sont centrées dans les flasques 20 et 22 avec des jeux adaptés, de 0,03 à 0,05 mm dans l'exemple illustré, sur une rondelle 9 insérée dans le centrage 25 (voir ci-dessous en référence à la
Des pales 28 solidaires du flasque 22, formant une deuxième grille annulaire bordant extérieurement la première grille, sont montées sur le flasque annulaire 20 par des vis traversantes 29 logées dans des trous 29t. Ces vis permettent également le passage des efforts structuraux.
La commande des pales variables 24 est réalisée par l'intermédiaire de tiges 30 prolongeant solidairement la coupelle amont 17. Ces tiges 30 d'axe X'X sont montées dans un alésage cylindrique 32 du flasque amont 20 et centrées avec un jeu quasi-nul par des joints 30j montés dans des gorges 30g. En extrémité, chaque tige 30 présente une partie plate 31 articulée sur un levier d'entraînement 33 pincé par deux vis 35 sur cette partie plate 31. Les positions des extrémités 31 des tiges 30 sont ajustées avec des tolérances de jeux adaptées. La tige 30 présente également un orifice 30t dans lequel est introduite une goupille 36 qui permet de bloquer une rondelle 30u - de réglage de la position axiale des coupelles 17 et 27 - dans un anneau de blocage 12a formé dans le carter 12. Dans ce but, la goupille 36 solidarise la tige 30 et l'anneau de blocage 12a.The control of the
En fonctionnement, le levier 33 est entraîné par une couronne de commande 34 formant un trou cylindrique 38 de logement de la rotule sphérique 37 du levier 33 avec une tolérance de position axiale adaptée et un contact sur une génératrice de la rotule. Pour ce faire, la couronne de commande 34 est centrée sur des secteurs présentant des roulements à aiguilles 39. La couronne de commande 34, mise en rotation autour de l'axe moteur Y'Y par une biellette (non représentée), entraîne en rotation les leviers 33 qui coulissent dans les logements cylindriques 38 grâce à leur rotule 37. La profondeur des logements 38 est fonction de la course des leviers 33, elle-même fonction de l'intervalle de rotation des pales 24. Cette architecture est particulièrement adaptée à une rotation des pales pouvant aller jusqu'à +12° avec une fermeture de 50% de section, et jusqu'à -5 ° avec une ouverture de section de 20%. Les angles de position des tiges et donc des pales 24 en fonction des régimes de puissance pour fournir la compression d'air appropriée à ces régimes.In operation, the
En référence aux
La vue globale de la
Les pales 28 présentent un profil sensiblement plus épais en bord d'attaque Ba que celui des pales 24, respectivement 0.5 et 2.5 mm, afin de préserver une bonne tenue aux variations d'incidence lors de la rotation des pales mobiles 24. De plus, la loi d'angle squelette des pales 28 entre les bords d'attaque BA et de fuite BF est évolutive, permettant d'optimiser l'efficacité aérodynamique de la grille fixe par une récupération maximale de pression statique.The
En outre, les pales 28 de la grille fixe présentent une épaisseur maximale, de 7 mm dans l'exemple illustré, permettant de fixer le flasque 20 du diffuseur par des vis se logeant dans les trous 29t, tout en permettant le passage des efforts structuraux.In addition, the
Le flux d'air F circule le long d'une pale fixe 28 en extension radiale d'une pale mobile 24 et entre deux pales adjacentes de même nature, mobile ou fixe. Grâce au décentrage des pales mobiles 24 par rapport aux axes de rotation X'X de leurs coupelles 17, les variations des extensions radiales formées par ces pales mobiles 24 sont limitées par rapport à des variations d'extensions que devraient réaliser des pales centrées. Cette limitation permet d'améliorer les performances d'un compresseur centrifuge : elle permet d'éloigner la ligne de fonctionnement de la ligne de pompage, par décalage vers des débits plus bas, et d'élever cette ligne de fonctionnement près des maximas de rendement aux régimes plus élevés.The air flow F circulates along a fixed
Les extensions radiales des pales mobiles 24 au regard des pales fixes 28 sont illustrées par les schémas des
Aux faibles demandes de charge, le calage des pales mobiles 24 peut monter jusqu'à +12°, ce calage correspondant à une section de passage à l'entrée du col Sa, entre les pales 24 et 28, fermée de 50% par rapport au calage nominal correspondant à une section au col Sb. La
les pales fixes 28 sont calées en azimut par rapport aux pales 24 de la première grille mobile G1 de sorte à reprendre le sillage sur l'extrados Ex des pales de cette première grille G1.the fixed
Les extensions radiales des pales 24, limitées par la présence des pales fixes 28, permettent de conserver une maîtrise des jeux entre les coupelles 17 et 27 des pales 24 et les flasques 20 et 22, comme illustré par la
L'invention n'est pas limitée aux exemples décrits et représentés. Il est par exemple possible d'effectuer le calage des pales mobiles par réglage uniquement mécanique, individuel ou centralisé, ou par commande électrique, électronique avec ou sans régulation numérique.The invention is not limited to the examples described and shown. It is for example possible to set the pitch of the mobile blades by only mechanical adjustment, individual or centralized, or by electrical, electronic control with or without digital control.
Claims (10)
- An adaptation method for the air flow in a centrifugal compressor (10) of a turbine engine, consisting in providing a diffusion of the air through a first annular blade ring (G1) with variable pitch blades (24), radially bordered with a second annular blade ring (G2) having the same number of fixed pitch blades (28) with an equivalent extension, guiding the diffusion in the radial direction by coupling the blades (24, 28) of the two blade rings, the method being characterized in that each blade (24) of the first blade ring (G1) is driven into rotation (X'X) at distance of the blade (24).
- The adaptation method according to claim 1, wherein the variable pitch radial diffusion on a centrifugal compressor is coupled with a variable pitch power turbine distribution, the power distribution being either free with a downstream exchange or bound, either on an axial or centripetal way, with or without downstream exchange.
- A variable pitch turbine engine diffuser being able to implement the method according to claim 1 or 2, comprising a first annular blade ring (G1) with variable pitch blades (24) being radially bordered by a second annular blade ring (G2) with fixed pitch blades (28) of an equivalent extension and a same number of blades, forming successive diffusion channels by coupling of the blades (24, 28) of the two blade rings (G1, G2) in radial extensions, characterized in that each blade (24) of the first blade ring (G1) is driven by driving means (30, 33, 34) adapted to exert a proper rotation of the blade (24) off-centred with respect to the rotation axis thereof (X'X).
- The diffuser according to preceding claim, wherein each variable pitch blade (24) extends between two facing cups (17, 27) and in a parallel and off-centred way with respect to the common axis of the cups coinciding with the rotation axis (X'X).
- The diffuser according to any of claims 3 or 4, wherein each blade (24) is coupled with a driving rod (30) that presents at least one orifice (30t) into which a lock pin (36) is introduced for an adjustment washer (30u) for the axial position of the cups (17, 27).
- The diffuser according to preceding claim, wherein the rod (30) is integral with a lever (33) presenting a ball joint coupling housed within a cylindrical housing (38) of a control crown (34) adapted to drive into rotation around the motive axis (Y'Y) the lever (33) being adapted to slide in the cylindrical housing (38).
- The diffuser according to preceding claim, wherein the cylindrical housings (38) present a depth being a function of the stroke of the levers (33), itself being a function of the predetermined rotation interval of the blades (24).
- The diffuser according to any of claims 4 to 7, wherein the leading edge (24c) of each variable pitch blade (24) is close to the peripheries (17c, 27c) of the cups (17, 27), the distance from the blade (24) to the rotation axis (X'X) being higher than or equal to a mid-radius.
- The diffuser according to any of claims 3 to 8, wherein the fixed blades (28) of the second blade ring (G2) present a thicker leading edge profile (Ba) than the one (24c) of the blades (24) of the first blade ring (G1).
- The diffuser according to any of claims 3 to 9, wherein the pitch angles of the mobile blades (24) are comprised between +12° and -5° corresponding to a collar section (Sa, Sc) respectively to 50% and 120% with respect to the section corresponding to the nominal setting.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PL11730371.9T PL2558728T5 (en) | 2010-04-14 | 2011-04-13 | Method for adapting the air flow of a turbine engine having a centrifugal compressor and diffuser for implementing same |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1052827A FR2958967B1 (en) | 2010-04-14 | 2010-04-14 | METHOD FOR ADJUSTING TURBOMACHINE AIR FLOW WITH CENTRIFUGAL COMPRESSOR AND DIFFUSER THEREFOR |
PCT/FR2011/050846 WO2011128587A1 (en) | 2010-04-14 | 2011-04-13 | Method for adapting the air flow of a turbine engine having a centrifugal compressor and diffuser for implementing same |
Publications (3)
Publication Number | Publication Date |
---|---|
EP2558728A1 EP2558728A1 (en) | 2013-02-20 |
EP2558728B1 true EP2558728B1 (en) | 2019-07-24 |
EP2558728B2 EP2558728B2 (en) | 2022-10-12 |
Family
ID=43067161
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP11730371.9A Active EP2558728B2 (en) | 2010-04-14 | 2011-04-13 | Method for adapting the air flow of a turbine engine having a centrifugal compressor and diffuser for implementing same |
Country Status (10)
Country | Link |
---|---|
US (1) | US20130034425A1 (en) |
EP (1) | EP2558728B2 (en) |
JP (2) | JP2013524099A (en) |
KR (1) | KR20130079326A (en) |
CN (1) | CN102834622B (en) |
CA (1) | CA2794825C (en) |
FR (1) | FR2958967B1 (en) |
PL (1) | PL2558728T5 (en) |
RU (1) | RU2564158C2 (en) |
WO (1) | WO2011128587A1 (en) |
Families Citing this family (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN103925246B (en) * | 2013-01-11 | 2017-06-09 | 哈米尔顿森德斯特兰德公司 | For the compressor housing of air cycle machine |
US9546669B2 (en) | 2013-01-11 | 2017-01-17 | Hamilton Sundstrand Corporation | Compressor housing for an air cycle machine |
JP2014152637A (en) * | 2013-02-05 | 2014-08-25 | Mitsubishi Heavy Ind Ltd | Centrifugal compressor |
FR3003908B1 (en) * | 2013-03-28 | 2017-07-07 | Turbomeca | DIFFUSER WITH FINES OF A RADIAL OR MIXED COMPRESSOR |
GB2513666B (en) * | 2013-05-03 | 2015-07-15 | Dyson Technology Ltd | Compressor |
DE102015220333A1 (en) * | 2015-10-19 | 2017-04-20 | Rolls-Royce Deutschland Ltd & Co Kg | Device for adjusting a gap between the housing of an impeller and the impeller in a centrifugal compressor and a turbomachine |
US10458429B2 (en) | 2016-05-26 | 2019-10-29 | Rolls-Royce Corporation | Impeller shroud with slidable coupling for clearance control in a centrifugal compressor |
US10718222B2 (en) | 2017-03-27 | 2020-07-21 | General Electric Company | Diffuser-deswirler for a gas turbine engine |
BE1025194B1 (en) * | 2017-05-05 | 2018-12-07 | Safran Aero Boosters S.A. | TURBULENCE SENSOR IN A TURBOMACHINE COMPRESSOR |
CN111279084B (en) * | 2017-11-01 | 2021-04-30 | 株式会社Ihi | Centrifugal compressor |
EP3620658A1 (en) * | 2018-09-04 | 2020-03-11 | Siemens Aktiengesellschaft | Lid of a turbomachine housing, turbomachine housing with a lid, turbomachine and method for the manufacture of a lid |
US10989219B2 (en) | 2019-02-04 | 2021-04-27 | Honeywell International Inc. | Diffuser assemblies for compression systems |
CN112983846A (en) | 2019-12-02 | 2021-06-18 | 开利公司 | Centrifugal compressor and method for operating a centrifugal compressor |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2985427A (en) | 1955-11-25 | 1961-05-23 | Gen Electric | Adjustable blading for fluid flow machines |
US3029067A (en) | 1956-05-31 | 1962-04-10 | Garrett Corp | Variable area nozzle means for turbines |
US3101926A (en) | 1960-09-01 | 1963-08-27 | Garrett Corp | Variable area nozzle device |
US3588270A (en) | 1968-08-20 | 1971-06-28 | Escher Wyss Ltd | Diffuser for a centrifugal fluid-flow turbomachine |
Family Cites Families (49)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2733853A (en) * | 1956-02-07 | trumpler | ||
US2189252A (en) * | 1938-05-07 | 1940-02-06 | Reggio Ferdinando Carlo | Blower |
US2300766A (en) * | 1940-05-10 | 1942-11-03 | Bbc Brown Boveri & Cie | Multistage centrifugal compressor |
US2860827A (en) * | 1953-06-08 | 1958-11-18 | Garrett Corp | Turbosupercharger |
US2991982A (en) * | 1957-09-12 | 1961-07-11 | Sigurd O Johnson | Centrifugal fluid moving device |
US3069070A (en) * | 1961-11-14 | 1962-12-18 | Worthington Corp | Diffuser vane system for turbomachinery |
US3372862A (en) * | 1965-10-22 | 1968-03-12 | Laval Turbine | Centrifugal compressor |
US3957392A (en) * | 1974-11-01 | 1976-05-18 | Caterpillar Tractor Co. | Self-aligning vanes for a turbomachine |
DE2945556C2 (en) * | 1979-11-10 | 1986-08-14 | Mbk Maschinenbau Gmbh, 7964 Kisslegg | Machine for the production of reinforcement bodies for precast concrete parts, in particular pipes |
FR2485102A1 (en) * | 1980-05-30 | 1981-12-24 | Neyrpic | Distribution control vanes appts. for high head water turbine - uses pair of thin blades in place of single heavy vane for more precise control of water flow and better sealing |
US4299535A (en) * | 1980-11-24 | 1981-11-10 | The Trane Company | Fan inlet guide vane assembly |
US4770605A (en) * | 1981-02-16 | 1988-09-13 | Mitsubishi Jukogyo Kabushiki Kaisha | Diffuser device in a centrifugal compressor and method for manufacturing the same |
US4403913A (en) * | 1981-11-03 | 1983-09-13 | Helsingoer Vaerft A/S | Guide blade arrangement for adjustable guide blades |
DE3147240A1 (en) * | 1981-11-28 | 1983-06-09 | Mannesmann Rexroth GmbH, 8770 Lohr | RADIAL PISTON MACHINE |
US4654941A (en) * | 1984-04-20 | 1987-04-07 | The Garrett Corporation | Method of assembling a variable nozzle turbocharger |
JPS61126052U (en) * | 1985-01-29 | 1986-08-07 | ||
DE3516738A1 (en) * | 1985-05-09 | 1986-11-13 | Mtu Motoren- Und Turbinen-Union Friedrichshafen Gmbh, 7990 Friedrichshafen | FLOWING MACHINE |
US4804316A (en) * | 1985-12-11 | 1989-02-14 | Allied-Signal Inc. | Suspension for the pivoting vane actuation mechanism of a variable nozzle turbocharger |
US4741666A (en) * | 1985-12-23 | 1988-05-03 | Ishikawajima-Harima Jukogyo Kabushiki Kaisha | Variable displacement turbocharger |
US4693073A (en) * | 1986-07-18 | 1987-09-15 | Sundstrand Corporation | Method and apparatus for starting a gas turbine engine |
US4824325A (en) * | 1988-02-08 | 1989-04-25 | Dresser-Rand Company | Diffuser having split tandem low solidity vanes |
US5187935A (en) * | 1988-12-26 | 1993-02-23 | Honda Giken Kogyo Kabushiki Kaisha | Engine control device |
US5072503A (en) * | 1990-01-08 | 1991-12-17 | Milletics, Bell And Clower | Method for disassembling an inner socket assembly |
DE4016195C1 (en) * | 1990-05-19 | 1991-05-23 | Mtu Muenchen Gmbh | |
US5207559A (en) | 1991-07-25 | 1993-05-04 | Allied-Signal Inc. | Variable geometry diffuser assembly |
DE4231452C2 (en) * | 1992-09-19 | 1994-11-03 | Gutehoffnungshuette Man | Turbo compressor with an outlet housing for the opposite direction of rotation |
FR2696210B1 (en) | 1992-09-25 | 1994-10-28 | Turbomeca | System for adjusting the air supply conditions of a turbomachine, centrifugal compressor comprising an adjustment system and auxiliary power unit comprising such a compressor. |
DE4309637A1 (en) * | 1993-03-25 | 1994-09-29 | Abb Management Ag | Radially flow-through turbocharger turbine |
DE4309636C2 (en) * | 1993-03-25 | 2001-11-08 | Abb Turbo Systems Ag Baden | Radially flow-through turbocharger turbine |
CA2149576A1 (en) * | 1994-05-19 | 1995-11-20 | Hideomi Harada | Surge detection device and turbomachinery therewith |
EP0719944B1 (en) * | 1994-12-28 | 2002-05-29 | Ebara Corporation | Turbomachinery having a variable angle flow guiding device |
US5730580A (en) * | 1995-03-24 | 1998-03-24 | Concepts Eti, Inc. | Turbomachines having rogue vanes |
DE19752534C1 (en) * | 1997-11-27 | 1998-10-08 | Daimler Benz Ag | Radial flow turbocharger turbine for internal combustion engine |
DE19817705C2 (en) * | 1998-04-21 | 2001-02-15 | Man Turbomasch Ag Ghh Borsig | Extraction of cooling air from the diffuser part of a compressor in a gas turbine |
DE19838754C1 (en) * | 1998-08-26 | 2000-03-09 | Daimler Chrysler Ag | Exhaust gas turbocharger for an internal combustion engine |
US6086327A (en) * | 1999-01-20 | 2000-07-11 | Mack Plastics Corporation | Bushing for a jet engine vane |
JP3686300B2 (en) * | 2000-02-03 | 2005-08-24 | 三菱重工業株式会社 | Centrifugal compressor |
JP2001329851A (en) * | 2000-05-19 | 2001-11-30 | Mitsubishi Heavy Ind Ltd | Variable nozzle mechanism for variable displacement turbine |
JP3659869B2 (en) * | 2000-05-22 | 2005-06-15 | 三菱重工業株式会社 | Variable capacity turbine |
DE10029640C2 (en) * | 2000-06-15 | 2002-09-26 | 3K Warner Turbosystems Gmbh | Exhaust gas turbocharger for an internal combustion engine |
JP3776740B2 (en) * | 2001-03-26 | 2006-05-17 | 三菱重工業株式会社 | Manufacturing method of variable capacity turbine component and structure of component |
JP3933455B2 (en) * | 2001-11-30 | 2007-06-20 | 株式会社小松製作所 | Variable turbocharger |
EP1394363B1 (en) * | 2002-08-26 | 2006-03-01 | BorgWarner Inc. | Variable guide vane system for a turbine unit |
DE50209301D1 (en) * | 2002-11-11 | 2007-03-08 | Borgwarner Inc | Guiding gratings of variable geometry |
EP1426563A1 (en) * | 2002-12-03 | 2004-06-09 | BorgWarner Inc. | Turbocharger with ceramic or metallic seal between the turbine and the bearing casing |
FR2896012B1 (en) * | 2006-01-06 | 2008-04-04 | Snecma Sa | ANTI-WEAR DEVICE FOR A TURNBUCKLE COMPRESSOR VARIABLE TUNING ANGLE GUIDING PIVOT PIVOT |
EP1811135A1 (en) * | 2006-01-23 | 2007-07-25 | ABB Turbo Systems AG | Variable guiding device |
GB0707501D0 (en) * | 2007-04-18 | 2007-05-30 | Imp Innovations Ltd | Passive control turbocharger |
WO2010101426A2 (en) * | 2009-03-05 | 2010-09-10 | 주식회사 에어젠 | Air compressor, and flow control method for an air compressor |
-
2010
- 2010-04-14 FR FR1052827A patent/FR2958967B1/en active Active
-
2011
- 2011-04-13 WO PCT/FR2011/050846 patent/WO2011128587A1/en active Application Filing
- 2011-04-13 CA CA2794825A patent/CA2794825C/en not_active Expired - Fee Related
- 2011-04-13 US US13/640,978 patent/US20130034425A1/en not_active Abandoned
- 2011-04-13 JP JP2013504319A patent/JP2013524099A/en active Pending
- 2011-04-13 KR KR1020127025210A patent/KR20130079326A/en not_active Application Discontinuation
- 2011-04-13 PL PL11730371.9T patent/PL2558728T5/en unknown
- 2011-04-13 CN CN201180018458.4A patent/CN102834622B/en active Active
- 2011-04-13 RU RU2012148378/06A patent/RU2564158C2/en not_active IP Right Cessation
- 2011-04-13 EP EP11730371.9A patent/EP2558728B2/en active Active
-
2016
- 2016-11-04 JP JP2016215929A patent/JP6483074B2/en not_active Expired - Fee Related
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2985427A (en) | 1955-11-25 | 1961-05-23 | Gen Electric | Adjustable blading for fluid flow machines |
US3029067A (en) | 1956-05-31 | 1962-04-10 | Garrett Corp | Variable area nozzle means for turbines |
US3101926A (en) | 1960-09-01 | 1963-08-27 | Garrett Corp | Variable area nozzle device |
US3588270A (en) | 1968-08-20 | 1971-06-28 | Escher Wyss Ltd | Diffuser for a centrifugal fluid-flow turbomachine |
Also Published As
Publication number | Publication date |
---|---|
CN102834622B (en) | 2016-02-10 |
RU2012148378A (en) | 2014-05-20 |
RU2564158C2 (en) | 2015-09-27 |
KR20130079326A (en) | 2013-07-10 |
US20130034425A1 (en) | 2013-02-07 |
CN102834622A (en) | 2012-12-19 |
PL2558728T3 (en) | 2019-10-31 |
CA2794825C (en) | 2018-06-12 |
FR2958967A1 (en) | 2011-10-21 |
JP6483074B2 (en) | 2019-03-13 |
CA2794825A1 (en) | 2011-10-20 |
JP2017061936A (en) | 2017-03-30 |
EP2558728B2 (en) | 2022-10-12 |
WO2011128587A1 (en) | 2011-10-20 |
EP2558728A1 (en) | 2013-02-20 |
PL2558728T5 (en) | 2023-02-06 |
FR2958967B1 (en) | 2013-03-15 |
JP2013524099A (en) | 2013-06-17 |
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