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WO2013163662A1 - Diffuseur de compresseur à aubes à sections transversales variables - Google Patents

Diffuseur de compresseur à aubes à sections transversales variables Download PDF

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Publication number
WO2013163662A1
WO2013163662A1 PCT/US2013/043968 US2013043968W WO2013163662A1 WO 2013163662 A1 WO2013163662 A1 WO 2013163662A1 US 2013043968 W US2013043968 W US 2013043968W WO 2013163662 A1 WO2013163662 A1 WO 2013163662A1
Authority
WO
WIPO (PCT)
Prior art keywords
vanes
compressor diffuser
meridional length
meridional
diffuser
Prior art date
Application number
PCT/US2013/043968
Other languages
English (en)
Inventor
Shakeel Nasir
Original Assignee
Electro-Motive Diesel, Inc.
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Electro-Motive Diesel, Inc. filed Critical Electro-Motive Diesel, Inc.
Priority to CN201380021346.3A priority Critical patent/CN104350286A/zh
Publication of WO2013163662A1 publication Critical patent/WO2013163662A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
    • 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 present disclosure is directed to a diffuser and, more particularly, to a compressor diffuser having vanes with variable cross-sections.
  • Internal combustion engines such as, for example, diesel engines, gasoline engines, and gaseous fuel powered engines are supplied with a mixture of air and fuel for subsequent combustion within the engines that generates a mechanical power output.
  • each engine can be equipped with a turbocharged air induction system.
  • a turbocharged air induction system includes a turbocharger that uses exhaust from the engine to compress air flowing into the engine, thereby forcing more air into a combustion chamber of the engine than the engine could otherwise draw into the combustion chamber. This increased supply of air allows for increased fuelling, resulting in an increased power output.
  • a turbocharged engine typically produces more power than the same engine without
  • a conventional turbocharger includes a compressor housing, a centrifugal compressor wheel centrally disposed within the housing and driven to rotate by a connected turbine wheel, and a stationary diffuser (vaned or vaneless) situated at a peripheral outlet of the compressor wheel.
  • a vaned diffuser is typically ring-shaped and includes protruding vanes that are angled relative to a radial flow path of air exiting blades of the compressor wheel. The vanes in the diffuser create restricted passages for the air that cause the air to slow down, trading velocity for an increase in pressure.
  • FIG. 516 An exemplary compressor diffuser is disclosed in U.S. Patent No. 5,178,516 of Nakagawa et al. that issued on 12 January 1993 (the '516 patent).
  • the '516 patent describes a vaned diffuser having a plurality of stator blades radially arranged around the periphery of a compressor wheel, and a plurality of smaller auxiliary blades interleaved with the stator blades.
  • the auxiliary and stator blades are curved along their length and have vertical walls that extend orthogonally between a hub surface of the diffuser and a mating shroud.
  • the diffuser of the '516 patent may be adequate for some applications, it may still be less than optimal.
  • the blades of the '516 patent have orthogonal walls, the channels between the blades formed by the walls of the blades have generally rectangular cross-sections. This cross- sectional shape may allow for a non-uniform distribution of airflow, pressure, and velocity within the channels, and such distributions can result in a reduced efficiency and/or range of the associated turbocharger.
  • the diffuser of the present disclosure solves one or more of the problems set forth above and/or other problems of the prior art. Summary
  • the present disclosure is directed to a compressor diffuser.
  • the compressor diffuser may include a ring-shaped generally flat plate, a plurality of first vanes disposed radially around an upper surface of the plate, and a plurality of second vanes shorter than the first vanes.
  • Each of the second vanes may be connected to the plate between adjacent first vanes.
  • the first and second vanes may each include a high-pressure side and an opposing low- pressure side.
  • Each of the first and second vanes may tilt towards one of its corresponding high- and low-pressure sides at a lean angle that changes along its meridional length.
  • the present disclosure is directed to another compressor diffuser.
  • This compressor diffuser may include a ring-shaped generally flat plate, a plurality of first vanes disposed radially around an upper surface of the plate, and a plurality of second vanes shorter than the first vanes. Each of the second vanes may be connected to the plate between adjacent first vanes. A density of the first and second vanes may vary relative to an annular position around the plate.
  • Fig. 1 is a pictorial illustration of an exemplary disclosed engine
  • Fig. 2 is a cross-sectional illustration of an exemplary disclosed turbocharger that may be used in conjunction with the engine of Fig. 1;
  • Fig. 3 is a pictorial illustration of an exemplary disclosed diffuser that may be used in conjunction with the turbocharger of Fig. 2;
  • Fig. 4 is a pictorial illustration of exemplary disclosed vanes that may be used in conjunction with the diffuser of Fig. 3;
  • Figs. 5 and 6 are charts associated with exemplary disclosed geometry of the vanes of Fig. 4.
  • Fig. 1 illustrates an engine 10 equipped with an air induction system 12 and an exhaust system 14.
  • engine 10 is depicted and described as a two-stroke diesel engine.
  • engine 10 may be another type of internal combustion engine such as, for example, a two- or four-stroke gasoline or gaseous fuel-powered engine.
  • Engine 10 may include an engine block 16 that at least partially defines a plurality of cylinders 18.
  • a piston (not shown) may be slidably disposed within each cylinder 18 to reciprocate between a top-dead- center position and a bottom-dead-center position, and a cylinder head (not shown) may be associated with each cylinder 18.
  • Cylinder 18, the piston, and the cylinder head may form a combustion chamber.
  • engine 10 includes twenty such combustion chambers arranged in two separate banks (only one shown in Fig. 1). However, it is contemplated that engine 10 may include a greater or lesser number of combustion chambers and that the combustion chambers may be disposed in an "in-line” configuration, in a "V” configuration, in an opposing piston configuration, or in any other suitable configuration.
  • Air induction system 12 may include components configured to introduce charged air into the combustion chambers of engine 10.
  • air induction system 12 may include an induction manifold (not shown - located between the opposing banks of combustion chambers) fluidly connected along its length to the combustion chambers, one or more compressors 24 in fluid communication with an end of the induction manifold, and, in some
  • an air cooler located downstream of compressors 24 and upstream of the combustion chambers. It is contemplated that additional components may be included within air induction system 12, if desired, such as valving, one or more air cleaners, one or more waste gates, a control system, a bypass circuit, and other means for introducing charged air into engine 10. It is also contemplated that the air cooler may be omitted, if desired.
  • Each compressor 24 of engine 10 may embody a fixed geometry centrifugal-type compressor that is mechanically driven to compress air flowing into engine 10 to a predetermined pressure level.
  • Compressors 24, if more than one is included within air induction system 12, may be disposed in a series or parallel relationship and fluidly connected to engine 10 via the induction manifold.
  • Exhaust system 14 may be configured to recuperate energy from the exhaust flowing out of the combustion chambers of engine 10.
  • exhaust system 14 may include an exhaust manifold 26 fluidly connected along its length to the combustion chambers, and one or more turbines 28 in fluid communication with an end of exhaust manifold 26.
  • Turbines 28, if more than one is included within exhaust system 14, may be connected in a series or parallel relationship.
  • compressor 24 and turbine 28 may each include an associated shroud 34, 36 configured to house corresponding compressor and turbine wheels 38, 40 that are connected to each other via a common shaft 42.
  • Each shroud 34, 36 may generally include an inlet 44, an outlet 46, and a scroll 48 connecting inlet 44 to outlet 46.
  • Inlets 44 may be axially oriented, while outlets 46 may be radially oriented.
  • compressor wheel 38 is rotated, air may be drawn axially in toward a center of compressor wheel 38. Blades 49 of compressor wheel 38 may then push the air radially outward in a spiraling fashion through scroll 48 and into the induction manifold (referring to Fig. 1).
  • turbine wheel 40 As exhaust from exhaust manifold 26 is directed axially inward to turbine wheel 40, the exhaust may push against blades 50 of turbine wheel 40 causing turbine wheel 40 to rotate and drive compressor wheel 38 via shaft 42. After passing through turbine wheel 40, the exhaust may spiral radially outward through outlet 46.
  • Compressor and turbine wheels 38, 40 may embody conventional wheels, with any number and configuration of blades 49, 50 radially disposed on a pressure face of corresponding wheel bases.
  • Shroud 34 associated with compressor 24 may include a diffuser 52 located within the outward radial flow path at a periphery of compressor wheel 38.
  • diffuser 52 may include, among other things, a ring-shaped generally flat plate 54 having a plurality of main vanes 56 and a plurality of splitter vanes 58. As shown in Fig.
  • each of main and splitter vanes 56, 58 may include a lower face (also known as a hub face) 60 that is connected to plate 54, an opposing upper face (also known as a shroud face) 62 that engages an inner surface of shroud 34, a leading edge 64 located close to compressor wheel 38, an opposing a trailing edge 66 located away from compressor wheel 38, a low-pressure side (also known as the suction side) 68, and an opposing high-pressure side (also known as the pressure side) 70.
  • a lower face also known as a hub face
  • an opposing upper face also known as a shroud face
  • a leading edge 64 located close to compressor wheel 38
  • an opposing a trailing edge 66 located away from compressor wheel 38
  • a low-pressure side also known as the suction side
  • an opposing high-pressure side also known as the pressure side
  • a height H of main and splitter vanes 56, 58 may refer to an orthogonal distance between lower and upper faces 60, 62.
  • a chord length Lc (shown in Fig. 3) may refer to a straight line distance between leading and trailing edges 64, 66.
  • a meridional length L M (shown in Fig. 3) may refer to a distance between leading and trailing edges 64, 66 of main and splitter vanes 56, 58 along a camber line passing through a lengthwise center of the respective vanes.
  • a thickness T may refer to a distance between low- and high-pressure sides 68, 70 that is generally orthogonal to the curving line.
  • a spacing S (shown in Fig.
  • An elliptical ratio of main and splitter vanes 56, 58 may be defined as the ratio of the focal length of the elliptical shape at leading edge 64 or trailing edge 66 divided by one -half of the width of the elliptical shape at a point of tangency with low- and high-pressure sides 68, 70.
  • main and splitter vanes 56, 58 has been selected to provide a desired flow uniformity through diffuser 52 that results in improved efficiency and range of turbocharger 30.
  • splitter vanes 58 are shorter than main vanes 56.
  • Leading edges 64 of splitter vanes 58 are located radially outward of leading edges 64 of main vanes 56 (e.g., at a radial location that is about 25-55% of the meridional length L M of main vanes 56 from leading edge 64 to trailing edge 66), and trailing edges 66 are generally radially aligned.
  • splitter vane 58 may be located between adjacent main vanes 56 (i.e., between the low-pressure side 68 of one main vane 56 and the high-pressure side 70 of an adjacent main vane 56) and closer to the high-pressure side 70 than to the low-pressure side 68. That is, splitter vanes 58 may be asymmetrically located relative to main vanes 56, although the asymmetry should be capped at about 5% relative to a center line located halfway between the adjacent main vanes 56.
  • the solidity ratio of main and splitter vanes 56, 58 may be about .7- 1.4, with about 8 to 18 pairs of vanes 56, 58.
  • plate 54 may have a ring ratio (i.e., ratio of outer diameter to inner diameter) of about 1.3-1.6.
  • annular density of main and splitter vanes 56, 58 may also be asymmetric, if desired.
  • the tongue of scroll 48 may be known to cause flow disruption (e.g., turbulence), and the higher density of vanes in this area may help to improve a uniformity of the flow.
  • Leading and trailing edges 64, 66 of main and/or splitter vanes 56, 58 may be rounded or tapered.
  • leading edges 64 may have an elliptical shape, with a leading edge elliptical ratio of about 2-6: 1 for main vanes 56 and about 4-10: 1 for splitter vanes 58.
  • trailing edges 66 may also have an elliptical shape, with a trailing edge elliptical ratio of about 2-4: 1.
  • main and splitter vanes 56, 58 may increase within the vanes accordingly to a height of the vanes between hub face 60 and shroud face 62 (i.e., main and splitter vanes 56, 58 may have leading and/or trailing edges 64, 66 that become narrower at shroud faces 62).
  • Main and splitter vanes 56, 58 may tilt toward one of their corresponding low- and high-pressure sides 68, 70, such that a cross-section of channels formed between these vanes is generally oblique and/or irregular. As shown in the exemplary embodiment of Fig. 4, main and splitter vanes 56, 58 tilt toward their respective low-pressure sides 68, with a lean angle a (the interior angle that main and splitter vanes 56, 58 make in a height direction relative to an upper planar surface of plate 54) that varies along the meridional length L M .
  • a the interior angle that main and splitter vanes 56, 58 make in a height direction relative to an upper planar surface of plate 54
  • Main and splitter vanes 56, 58 may also curve along their lengths, each forming a corresponding meridional vane angle ⁇ (i.e., angle formed between a radial line drawn from a center of plate 54 to a corresponding tangent on the camber line of the vane).
  • Meridional vane angle ⁇ may change along the meridional length L M , as well as along the height H of main and splitter vanes 56, 58, and have an absolute value within the range of about 36-76 degrees.
  • Fig. 5 shows a first curve 500 corresponding to the meridional vane angle ⁇ at hub face 60, and a second curve 510 corresponding to the meridional vane angle ⁇ at shroud face 62.
  • the meridional vane angle ⁇ at shroud face 62 may generally be larger than the meridional vane angle ⁇ at hub face 60 (i.e., main and splitter vanes 56, 58 may be more vertical at shroud face 62).
  • the distribution may alternatively be such that the meridional vane angle ⁇ is larger at hub face 60, if desired.
  • the meridional vane angle a at shroud face 62 may generally mirror the meridional vane angle ⁇ at hub face 60, with the meridional vane angle ⁇ at both faces reaching a maximum at about 15-20% of the meridional length L M from leading edge 64 to trailing edge 66 and a minimum at a trailing edge 66.
  • the meridional vane angle ⁇ for main vanes 56 may be about the same as the meridional vane angle ⁇ for splitter vanes 58, relative to the percent of the meridional length L M from leading edge 64 to trailing edge 66 of the respective vanes.
  • the meridional vane angle ⁇ of main vanes 56 at about 50% of their meridional length L M from leading edge 64 to trailing edge 66 may be about the same as the meridional vane angle ⁇ of splitter vanes 58 at about 50% of the meridional length LM of main vanes 56.
  • Fig. 6 shows a curve 600 corresponding to the thickness T of main and splitter vanes 56, 58 relative to the meridional length LM of main vanes 56.
  • the thickness of main and splitter vanes 56, 58 may reach a maximum at about 25-40% of the meridional length L M and be thinnest at trailing edge 66.
  • the thickness T of main vanes 56 may be about the same as the thickness T of splitter vanes 58, relative to the percent of the meridional length LM from leading edge 64 to trailing edge 66 of main vanes 56.
  • the disclosed diffuser may be implemented into any turbocharger and power system application where increased efficiency and range is desired.
  • the disclosed geometry of main and splitter vanes 56, 58 may be selected to improve flow uniformity, choke margin, and surge margin. Improved flow uniformity may result in a greater flow rate of compressed air with fewer losses.

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

Abstract

La présente invention concerne un diffuseur (52) destiné à être utilisé avec un compresseur (24). Le diffuseur de compresseur selon l'invention peut comporter une plaque (54) généralement plate en forme d'anneau, une pluralité de premières aubes (56) disposées radialement autour d'une surface supérieure de la plaque, et une pluralité de secondes aubes (58) plus courtes que les premières aubes. Chacune des secondes aubes peut être raccordée à la plaque entre les premières aubes adjacentes. Chacune des premières et des secondes aubes peut présenter un côté haute pression (70) et un côté basse pression (68) opposé, et chacune peut s'incliner vers l'un de ses côtés haute pression et basse pression correspondants à un angle d'inclinaison qui change le long de sa longueur méridionale.
PCT/US2013/043968 2012-04-23 2013-06-04 Diffuseur de compresseur à aubes à sections transversales variables WO2013163662A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201380021346.3A CN104350286A (zh) 2012-04-23 2013-06-04 具有包括可变横截面的翼片的压缩机扩散器

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/453,626 2012-04-23
US13/453,626 US20130280060A1 (en) 2012-04-23 2012-04-23 Compressor diffuser having vanes with variable cross-sections

Publications (1)

Publication Number Publication Date
WO2013163662A1 true WO2013163662A1 (fr) 2013-10-31

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ID=48672806

Family Applications (1)

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PCT/US2013/043968 WO2013163662A1 (fr) 2012-04-23 2013-06-04 Diffuseur de compresseur à aubes à sections transversales variables

Country Status (3)

Country Link
US (1) US20130280060A1 (fr)
CN (1) CN104350286A (fr)
WO (1) WO2013163662A1 (fr)

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103671193B (zh) * 2013-11-30 2016-01-20 西安交通大学 一种回流器叶片可振荡的离心压缩机
WO2015097632A1 (fr) * 2013-12-23 2015-07-02 Fisher & Paykel Healthcare Limited Soufflante pour appareil respiratoire
KR102586852B1 (ko) 2015-04-30 2023-10-06 컨셉츠 엔알이씨, 엘엘씨 디퓨저 내 바이어스된 통로들 및 그러한 디퓨저를 설계하기 위한 대응되는 방법
WO2017028319A1 (fr) * 2015-08-20 2017-02-23 深圳智慧能源技术有限公司 Compresseur centrifuge et son rouet
DE102016201256A1 (de) * 2016-01-28 2017-08-03 Siemens Aktiengesellschaft Strömungsmaschine mit beschaufeltem Diffusor
KR20170124291A (ko) * 2016-05-02 2017-11-10 삼성전자주식회사 팬 모터 및 이를 갖춘 진공 청소기
CN106499670B (zh) * 2016-10-28 2017-10-10 扬州大学 带副导叶的泵装置出水流道
JP2020514610A (ja) 2016-12-23 2020-05-21 ボーグワーナー インコーポレーテッド ターボチャージャー及びタービンホイール
EP3364039A1 (fr) * 2017-02-21 2018-08-22 Siemens Aktiengesellschaft Étage de retour
DE102017203230A1 (de) * 2017-02-28 2018-08-30 Siemens Aktiengesellschaft Diffusor
CN107061321B (zh) * 2017-03-15 2018-12-11 清华大学 采用安装角和稠度耦合可变的非对称有叶扩压器的压气机
DE102017118950A1 (de) * 2017-08-18 2019-02-21 Abb Turbo Systems Ag Diffusor für einen Radialverdichter
US10989219B2 (en) 2019-02-04 2021-04-27 Honeywell International Inc. Diffuser assemblies for compression systems
CN110701111B (zh) * 2019-10-25 2021-02-09 江汉大学 一种利用分流叶片减少轴流风机导流叶片总压损失的方法
CN113074138B (zh) * 2020-01-06 2022-05-17 广东威灵电机制造有限公司 扩压装置、风机及吸尘器
WO2021139508A1 (fr) 2020-01-06 2021-07-15 广东威灵电机制造有限公司 Diffuseur, appareil d'alimentation en air et équipement de collecte de poussière
IT202000001216A1 (it) * 2020-01-22 2021-07-22 Nuovo Pignone Tecnologie Srl Un diffusore con passo delle pale di diffusore non costante e turbomacchina centrifuga comprendente detto diffusore
EP4093978A1 (fr) 2020-01-23 2022-11-30 Nuovo Pignone Tecnologie - S.R.L. Canal de retour à pas d'aubes de canal de retour non constant et turbomachine centrifuge comprenant ledit canal de retour
CN112343864B (zh) * 2020-11-10 2022-11-04 江西省子轩科技有限公司 一种工业应用压缩机组
WO2022117215A1 (fr) * 2020-12-04 2022-06-09 Cummins Ltd Agencement d'aube, compresseur, programme informatique, et procédés de fabrication et de conception associés
GB2616217A (en) * 2020-12-04 2023-08-30 Cummins Ltd Compressor

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0280205A2 (fr) * 1987-02-19 1988-08-31 BMW ROLLS-ROYCE GmbH Compresseur radial
US5178516A (en) 1990-10-02 1993-01-12 Hitachi, Ltd. Centrifugal compressor
US20070059170A1 (en) * 2005-09-13 2007-03-15 Ingersoll-Rand Company Diffuser for a centrifugal compressor
US20110194931A1 (en) * 2010-02-05 2011-08-11 Cameron International Corporation Centrifugal compressor diffuser vanelet

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4790720A (en) * 1987-05-18 1988-12-13 Sundstrand Corporation Leading edges for diffuser blades
EP0305879B1 (fr) * 1987-09-01 1993-07-21 Hitachi, Ltd. Diffuseur pour compresseur centrifuge
US5368440A (en) * 1993-03-11 1994-11-29 Concepts Eti, Inc. Radial turbo machine
US7448852B2 (en) * 2005-08-09 2008-11-11 Praxair Technology, Inc. Leaned centrifugal compressor airfoil diffuser
JP4795912B2 (ja) * 2006-10-30 2011-10-19 三菱重工業株式会社 可変ディフューザ及び圧縮機
JP4265656B2 (ja) * 2007-01-15 2009-05-20 トヨタ自動車株式会社 遠心圧縮機
CN201461538U (zh) * 2009-07-30 2010-05-12 大同北方天力增压技术有限公司 一种抛物线型叶片式扩压器

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0280205A2 (fr) * 1987-02-19 1988-08-31 BMW ROLLS-ROYCE GmbH Compresseur radial
US5178516A (en) 1990-10-02 1993-01-12 Hitachi, Ltd. Centrifugal compressor
US20070059170A1 (en) * 2005-09-13 2007-03-15 Ingersoll-Rand Company Diffuser for a centrifugal compressor
US20110194931A1 (en) * 2010-02-05 2011-08-11 Cameron International Corporation Centrifugal compressor diffuser vanelet

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CN104350286A (zh) 2015-02-11
US20130280060A1 (en) 2013-10-24

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