EP2558728B2 - Procédé d'adaptation de débit d'air de turbomachine à compresseur centrifuge et diffuseur de mise en oeuvre - Google Patents

Procédé d'adaptation de débit d'air de turbomachine à compresseur centrifuge et diffuseur de mise en oeuvre Download PDF

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Publication number
EP2558728B2
EP2558728B2 EP11730371.9A EP11730371A EP2558728B2 EP 2558728 B2 EP2558728 B2 EP 2558728B2 EP 11730371 A EP11730371 A EP 11730371A EP 2558728 B2 EP2558728 B2 EP 2558728B2
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EP
European Patent Office
Prior art keywords
blades
blade
diffuser
cups
pitch
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP11730371.9A
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German (de)
English (en)
French (fr)
Other versions
EP2558728A1 (fr
EP2558728B1 (fr
Inventor
Pierre Biscay
Patrick Marconi
Hubert Hippolyte Vignau
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Helicopter Engines SAS
Original Assignee
Safran Helicopter Engines SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
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Application filed by Safran Helicopter Engines SAS filed Critical Safran Helicopter Engines SAS
Priority to PL11730371.9T priority Critical patent/PL2558728T5/pl
Publication of EP2558728A1 publication Critical patent/EP2558728A1/fr
Application granted granted Critical
Publication of EP2558728B1 publication Critical patent/EP2558728B1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F04D29/444—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • 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
    • 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
    • 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 application relates to a method for adapting the air flow of a turbomachine comprising a centrifugal compressor, in particular of helicopter turbine engines or auxiliary power units (abbreviated as APU) to a variable flow demand or mechanical or electrical power.
  • APU auxiliary power units
  • the method does not form part of the invention.
  • the invention 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 the engines of turbomachines and, more particularly, the adaptation of the flow of compressed air to respect the performance of the engines, whether they are turbine engines or APUs, in particular its consumption. specific (abbreviated as Cs) at partial load.
  • a general problem is to meet the pumping margin needs and to compensate for the reductions in compression ratio at the intermediate speeds of the turbine engines, as well as the variations in demand for compressed air flow and electrical power in the case of APUs.
  • IGV inlet guide vanes
  • variable timing is achieved by appropriate controls in conjunction with a control unit depending on the physical parameters involved (rotation speed, pressures, temperatures).
  • rotation speed rotation speed
  • pressures pressures
  • temperatures the ranges of pitch angles that the control system must cover require a high-power control actuator, lead to significant variations in the inlet and outlet diameters of the diffuser, which can generate high mechanical stresses between rotating (impeller) and static (variable-pitch radial diffuser) parts and reduces efficiency at part load (intermediate speed).
  • the invention aims to overcome these drawbacks, in particular by maintaining the efficiency of the compressor in order to substantially reduce the Cs while guaranteeing a sufficient pumping margin with better engine cycle efficiency at part load. To do this, it proposes an optimized process for variable diffusion of the air flow in a centrifugal compressor of turbomachines.
  • the application discloses a method, which does not form part of the invention, namely a method for the diffusion of variable air flow in a centrifugal compressor of turbomachine engines, consisting in providing a diffusion of the air at through a first annular grid of variable-pitch blades bordered radially by a second annular grid of the same number of fixed-pitch blades of equivalent extension, orienting the diffusion in the radial direction by coupling the blades of the two blades, each blade of the first blade being driven in rotation at a distance from the blade.
  • Turbomachines should be understood to mean turbine engines, in particular helicopter turbine engines with single-stage or two-stage centrifugal compressors, and APUs equipped with single- or two-stage power centrifugal compressors.
  • variable-pitch blades are substantially reduced by the presence of the fixed blading comprising real blades, which makes it possible to limit the efforts to vary their pitch as well as the clearances between the mobile blading and the support flange and therefore the upstream/downstream recirculations, which has the effect of reducing the deterioration of the pumping line and the pressure drops.
  • variable-pitch blades significantly reduces the variations in radial extension of these iso-diffusion blades: the increase on closing is less, thus promoting efficiency, at partial load and the decrease at lower opening also, which limits the mechanical stresses due to unsteady aerodynamic fluctuations by impeller/diffuser interaction.
  • a sufficient surge margin then allows the turbomachine to operate without the appearance of surge - offering a high acceleration capacity -, and the APU to cope with significant load variations, without using a wastegate, while maintaining the speed of rotation of the turbomachine and its pressure rate at levels close to their nominal values and providing a sufficient level of efficiency.
  • the method applies to turbomachines equipped with a power turbine, the variable-pitch radial diffusion on a centrifugal compressor, as defined above, is coupled to a variable-pitch power turbine distributor.
  • the power production can be carried out according to several configurations: free power turbine - or linked, of the axial or centripetal type, with or without downstream heat exchange.
  • the coupling between the diffuser and the variable-pitch distributor makes it possible to adapt the operating line to the reduction in flow, which improves the efficiency of the engine cycle (by a better pressure rate) and therefore the Cs of helicopter turbine engines and APUs.
  • variable-pitch turbine engine diffuser as defined in claim 1.
  • upstream and downstream refer to the direction of flow of the air flow in a turbine engine.
  • the centrifugal compressor 10 of a turbine engine such as a turbine engine, turbojet, turboprop or an APU, comprises a casing 12 coupled to a radial cover 14 of the impeller 16, the last centrifugal stage of the compressor, rotatably mounted on the motor shaft 18 along the Y'Y axis.
  • the air flow F circulates from the impeller 16 towards the annular diffuser 19, in an inlet stream converging by radial narrowing.
  • the diffuser 19 is defined between two upstream and downstream flanges 20 and 22.
  • the cover 14 is held by a clip 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, receive 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 suitable 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 the figure 5 ).
  • Blades 28 secured to flange 22, forming a second annular grid bordering the first grid on the outside, are mounted on 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 carried out by means of rods 30 integrally extending the upstream cup 17.
  • rods 30 of axis X′X are mounted in a cylindrical bore 32 of the upstream flange 20 and centered with almost zero clearance. by 30j seals mounted in 30g grooves.
  • each rod 30 has a flat part 31 hinged on a drive lever 33 pinched by two screws 35 on this flat part 31.
  • the positions of the ends 31 of the rods 30 are adjusted with suitable play tolerances.
  • the rod 30 also has an orifice 30t in which is inserted a pin 36 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 joint 37 of the lever 33 with a suitable axial position tolerance and 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 around the motor axis Y'Y by a connecting rod (not shown), rotates the levers 33 which slide in the cylindrical housings 38 thanks to their ball joint 37.
  • the depth of the housings 38 is a function of the stroke of the levers 33, itself a function of the range of rotation of the blades 24.
  • This architecture is particularly suitable for a blade rotation of up to +12° with a 50% section closure, and up to -5° with a 20% section opening.
  • a movable blade 24 is shown between the parallel cups 17, 27 and secured by welding 21 thereto, so that the blade extends parallel to the axis X'X of the facing cups.
  • 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 example shown.
  • the distance between the blade 24 and the axis X'X of the rod 30 is equal to approximately 80% of the radius of the cups in the example illustrated. This gives the blade 24 a strong off-centering relative 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 orifice 30t for locking the washer for adjusting the axial position of the cups 17 and 27. Its flat part 31 is traversed by holes 30a for receiving the mounting screws 35 at the control lever.
  • the global view of the picture 3 illustrates the upstream annular flange 20 equipped with annular grids 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 mobile blades 24.
  • the skeleton angle law of the blades 28 between the leading edges BA and trailing edges BF is scalable, making it possible to optimize the aerodynamic efficiency of the fixed grid by maximum recovery of static pressure.
  • the blades 28 of the fixed grid have a maximum thickness, of 7 mm in the example illustrated, making it possible to fix the flange 20 of the diffuser by screws fitting into 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 mobile blade 24 and between two adjacent blades of the same type, 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 mobile blades 24 are limited with respect to the variations of extensions that centered blades should achieve. 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 efficiency maxima. at higher speeds.
  • the radial extensions of the moving 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 mobile 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 pitch corresponding to a section of passage at the entrance to the neck Sa, between the blades 24 and 28, closed by 50% with respect to at the nominal setting corresponding to a neck section Sb.
  • the figure 4a illustrates the case of a 25% collapse associated with a setting of 6°, the neck section then being equal to 75% of the Sb section.
  • the timing adjustment can also go down to -5°.
  • the figure 4c illustrates the case of an opening of 2.5°, the neck section Sc then having a relative value of 110%.
  • the fixed blades 28 are set in azimuth with respect to the blades 24 of the first mobile grid G1 so as to resume the wake on the upper surface Ex of the blades of this first grid G1.
  • the clearance values remain less than or equal respectively to 0.02 mm (for J1 or J2), 0.10 mm (for J3) and 0.25 mm (for J4).
  • the clearance (together J1 and J2) of the blade 24 on the washer 9 therefore remains approximately 0.03 mm or slightly greater.
  • the invention is not limited to the examples described and represented. It is, for example, possible to effect the timing of the moving blades by solely mechanical adjustment, individual or centralized, or by electrical or electronic control with or without digital regulation.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP11730371.9A 2010-04-14 2011-04-13 Procédé d'adaptation de débit d'air de turbomachine à compresseur centrifuge et diffuseur de mise en oeuvre Active EP2558728B2 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL11730371.9T PL2558728T5 (pl) 2010-04-14 2011-04-13 Sposób dostosowywania natężenia przepływu powietrza w maszynie wirowej zawierającej sprężarkę odśrodkową i dyfuzor do realizacji tego sposobu

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1052827A FR2958967B1 (fr) 2010-04-14 2010-04-14 Procede d'adaptation de debit d'air de turbomachine a compresseur centrifuge et diffuseur de mise en oeuvre
PCT/FR2011/050846 WO2011128587A1 (fr) 2010-04-14 2011-04-13 Procédé d'adaptation de débit d'air de turbomachine à compresseur centrifuge et diffuseur de mise en oeuvre

Publications (3)

Publication Number Publication Date
EP2558728A1 EP2558728A1 (fr) 2013-02-20
EP2558728B1 EP2558728B1 (fr) 2019-07-24
EP2558728B2 true EP2558728B2 (fr) 2022-10-12

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ID=43067161

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EP11730371.9A Active EP2558728B2 (fr) 2010-04-14 2011-04-13 Procédé d'adaptation de débit d'air de turbomachine à compresseur centrifuge et diffuseur de mise en oeuvre

Country Status (10)

Country Link
US (1) US20130034425A1 (pl)
EP (1) EP2558728B2 (pl)
JP (2) JP2013524099A (pl)
KR (1) KR20130079326A (pl)
CN (1) CN102834622B (pl)
CA (1) CA2794825C (pl)
FR (1) FR2958967B1 (pl)
PL (1) PL2558728T5 (pl)
RU (1) RU2564158C2 (pl)
WO (1) WO2011128587A1 (pl)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9546669B2 (en) 2013-01-11 2017-01-17 Hamilton Sundstrand Corporation Compressor housing for an air cycle machine
CN103925246B (zh) * 2013-01-11 2017-06-09 哈米尔顿森德斯特兰德公司 用于空气循环机的压缩机壳体
JP2014152637A (ja) * 2013-02-05 2014-08-25 Mitsubishi Heavy Ind Ltd 遠心圧縮機
FR3003908B1 (fr) * 2013-03-28 2017-07-07 Turbomeca Diffuseur a ailettes d un compresseur radial ou mixte
GB2513666B (en) * 2013-05-03 2015-07-15 Dyson Technology Ltd Compressor
DE102015220333A1 (de) * 2015-10-19 2017-04-20 Rolls-Royce Deutschland Ltd & Co Kg Vorrichtung zur Einstellung eines Spaltes zwischen dem Gehäuse eines Laufrades und dem Laufrad in einem Radialverdichter und eine Turbomaschine
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 (fr) * 2017-05-05 2018-12-07 Safran Aero Boosters S.A. Capteur de turbulences dans un compresseur de turbomachine
WO2019087970A1 (ja) * 2017-11-01 2019-05-09 株式会社Ihi 遠心圧縮機
EP3620658A1 (de) * 2018-09-04 2020-03-11 Siemens Aktiengesellschaft Deckel eines turbomaschinengehäuses, turbomaschinengehäuse mit einem deckel, turbomaschine und verfahren zur herstellung eines deckels
US10989219B2 (en) 2019-02-04 2021-04-27 Honeywell International Inc. Diffuser assemblies for compression systems
CN112983846B (zh) 2019-12-02 2025-08-26 开利公司 离心压缩机和运行离心压缩机的方法
US12345162B2 (en) 2023-11-17 2025-07-01 Rolls-Royce Corporation Adjustable position impeller shroud for centrifugal compressors
US12345163B2 (en) 2023-11-17 2025-07-01 Rolls-Royce Corporation Travel stop for a tip clearance control system

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5207559A (en) † 1991-07-25 1993-05-04 Allied-Signal Inc. Variable geometry diffuser assembly

Family Cites Families (52)

* Cited by examiner, † Cited by third party
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
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
US2991982A (en) * 1957-09-12 1961-07-11 Sigurd O Johnson Centrifugal fluid moving device
US3101926A (en) 1960-09-01 1963-08-27 Garrett Corp Variable area nozzle 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
CH486636A (de) * 1968-08-20 1970-02-28 Escher Wyss Ag Diffusor einer Zentrifugalfördermaschine
US3957392A (en) * 1974-11-01 1976-05-18 Caterpillar Tractor Co. Self-aligning vanes for a turbomachine
DE2945556C2 (de) * 1979-11-10 1986-08-14 Mbk Maschinenbau Gmbh, 7964 Kisslegg Maschine zur Herstellung von Bewehrungskörpern für Betonfertigteile, insbesondere Rohre
FR2485102A1 (fr) * 1980-05-30 1981-12-24 Neyrpic Organe de distribution pour machine hydroelectrique de haute chute
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 (de) * 1981-11-28 1983-06-09 Mannesmann Rexroth GmbH, 8770 Lohr Radialkolbenmaschine
US4654941A (en) * 1984-04-20 1987-04-07 The Garrett Corporation Method of assembling a variable nozzle turbocharger
JPS61126052U (pl) * 1985-01-29 1986-08-07
DE3516738A1 (de) * 1985-05-09 1986-11-13 Mtu Motoren- Und Turbinen-Union Friedrichshafen Gmbh, 7990 Friedrichshafen Stroemungsmaschine
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 (pl) * 1990-05-19 1991-05-23 Mtu Muenchen Gmbh
DE4231452C2 (de) * 1992-09-19 1994-11-03 Gutehoffnungshuette Man Turbokompressor mit einem Austrittsgehäuse für entgegengesetzte Drehrichtung
FR2696210B1 (fr) * 1992-09-25 1994-10-28 Turbomeca Système de réglage des conditions d'alimentation en air d'une turbomachine, compresseur centrifuge comportant un système de réglage et groupe auxiliaire de puissance comportant un tel compresseur.
DE4309636C2 (de) * 1993-03-25 2001-11-08 Abb Turbo Systems Ag Baden Radialdurchströmte Abgasturboladerturbine
DE4309637A1 (de) * 1993-03-25 1994-09-29 Abb Management Ag Radialdurchströmte Abgasturboladerturbine
CA2149576A1 (en) * 1994-05-19 1995-11-20 Hideomi Harada Surge detection device and turbomachinery therewith
KR100388158B1 (ko) * 1994-12-28 2003-09-06 가부시키 가이샤 에바라 세이사꾸쇼 가변각유체안내장치를구비한터보기계장치
US5730580A (en) * 1995-03-24 1998-03-24 Concepts Eti, Inc. Turbomachines having rogue vanes
DE19752534C1 (de) * 1997-11-27 1998-10-08 Daimler Benz Ag Radialdurchströmte Abgasturboladerturbine
DE19817705C2 (de) * 1998-04-21 2001-02-15 Man Turbomasch Ag Ghh Borsig Kühlluftentnahme aus dem Diffusorteil eines Kompressors einer Gasturbine
DE19838754C1 (de) * 1998-08-26 2000-03-09 Daimler Chrysler Ag Abgasturbolader für eine Brennkraftmaschine
US6086327A (en) * 1999-01-20 2000-07-11 Mack Plastics Corporation Bushing for a jet engine vane
JP3686300B2 (ja) * 2000-02-03 2005-08-24 三菱重工業株式会社 遠心圧縮機
JP2001329851A (ja) * 2000-05-19 2001-11-30 Mitsubishi Heavy Ind Ltd 可変容量タービンの可変ノズル機構
JP3659869B2 (ja) * 2000-05-22 2005-06-15 三菱重工業株式会社 可変容量タービン
DE10029640C2 (de) * 2000-06-15 2002-09-26 3K Warner Turbosystems Gmbh Abgasturbolader für eine Brennkraftmaschine
JP3776740B2 (ja) * 2001-03-26 2006-05-17 三菱重工業株式会社 可変容量タービン構成部材の製作方法及び構成部材の構造
JP3933455B2 (ja) * 2001-11-30 2007-06-20 株式会社小松製作所 可変ターボ過給機
EP1394363B1 (de) * 2002-08-26 2006-03-01 BorgWarner Inc. Verstellbares Leitgitter für eine Turbineneinheit
EP1418311B1 (de) * 2002-11-11 2007-01-17 BorgWarner Inc. Leitgitter variabler Geometrie
EP1426563A1 (de) * 2002-12-03 2004-06-09 BorgWarner Inc. Turbolader mit keramischer oder metallischer Hitzeisolierung zwischen Turbinen- und Lagergehäuse
FR2896012B1 (fr) * 2006-01-06 2008-04-04 Snecma Sa Dispositif anti-usure pour pivot de guidage d'aube a angle de calage variable de compresseur de turbomachine
EP1811135A1 (de) * 2006-01-23 2007-07-25 ABB Turbo Systems AG Verstellbare Leitvorrichtung
GB0707501D0 (en) * 2007-04-18 2007-05-30 Imp Innovations Ltd Passive control turbocharger
US20110318182A1 (en) * 2009-03-05 2011-12-29 Airzen Co.,Ltd Gas compressor and method for controlling flow rate thereof

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5207559A (en) † 1991-07-25 1993-05-04 Allied-Signal Inc. Variable geometry diffuser assembly

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Publication number Publication date
JP2017061936A (ja) 2017-03-30
CA2794825A1 (fr) 2011-10-20
RU2012148378A (ru) 2014-05-20
FR2958967A1 (fr) 2011-10-21
US20130034425A1 (en) 2013-02-07
JP2013524099A (ja) 2013-06-17
CN102834622B (zh) 2016-02-10
CN102834622A (zh) 2012-12-19
EP2558728A1 (fr) 2013-02-20
EP2558728B1 (fr) 2019-07-24
FR2958967B1 (fr) 2013-03-15
JP6483074B2 (ja) 2019-03-13
RU2564158C2 (ru) 2015-09-27
KR20130079326A (ko) 2013-07-10
CA2794825C (fr) 2018-06-12
WO2011128587A1 (fr) 2011-10-20
PL2558728T3 (pl) 2019-10-31
PL2558728T5 (pl) 2023-02-06

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