WO2008035465A1 - Compresseur centrifuge - Google Patents

Compresseur centrifuge Download PDF

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Publication number
WO2008035465A1
WO2008035465A1 PCT/JP2007/052391 JP2007052391W WO2008035465A1 WO 2008035465 A1 WO2008035465 A1 WO 2008035465A1 JP 2007052391 W JP2007052391 W JP 2007052391W WO 2008035465 A1 WO2008035465 A1 WO 2008035465A1
Authority
WO
WIPO (PCT)
Prior art keywords
wall surface
diffuser
side wall
centrifugal compressor
diffuser passage
Prior art date
Application number
PCT/JP2007/052391
Other languages
English (en)
Japanese (ja)
Inventor
Koichi Sugimoto
Takashi Shiraishi
Hirotaka Higashimori
Hideyoshi Isobe
Original Assignee
Mitsubishi Heavy Industries, Ltd.
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 Mitsubishi Heavy Industries, Ltd. filed Critical Mitsubishi Heavy Industries, Ltd.
Priority to US11/989,241 priority Critical patent/US20100129209A1/en
Priority to EP07714007A priority patent/EP2072834A1/fr
Publication of WO2008035465A1 publication Critical patent/WO2008035465A1/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
    • F04D29/403—Casings; Connections of working fluid especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/002—Details, component parts, or accessories 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
    • F05D2210/00—Working fluids
    • F05D2210/10—Kind or type
    • F05D2210/12—Kind or type gaseous, i.e. compressible
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/52—Outlet
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S417/00—Pumps

Definitions

  • the present invention relates to a centrifugal compressor such as a turbocharger.
  • centrifugal compressor such as a turbocharger used for an internal combustion engine for automobiles is known.
  • FIG. 5A is a cross-sectional view showing a main part of a conventional centrifugal compressor.
  • the illustrated centrifugal compressor 10 compresses a fluid such as gas or air introduced from the outside of the housing 11 by rotating an impeller 13 having a large number of blades 12 in a housing 11.
  • the fluid flow (air flow) formed in this way is sent to the outside through the impeller outlet (hereinafter also referred to as “diffuser inlet”) 14, the diffuser passage 15 and the scroll 16 which is the outer peripheral end of the impeller 13.
  • reference numeral 17 in the figure denotes an axial center line around which the impeller 13 rotates.
  • the diffuser passage 15 described above is provided between the impeller outlet 14 and the scroll 16, and is a passage for recovering the static pressure by decelerating the airflow discharged from the impeller outlet 14.
  • the diffuser passage 15 is usually formed by a pair of opposed wall surfaces. In the following description, one of the pair of opposed wall surfaces is referred to as a shroud side wall surface 15a, and the other is referred to as a groove side wall surface 15b.
  • the mechanism for generating surging is considered to occur when the backflow region of the airflow reaches the outlet end of the diffuser passage 15.
  • the above-described backflow region is generated. It is considered that the raw material is caused by the flow on the compressor shroud side in the diffuser passage 15, that is, the flow distortion along the shroud side wall surface 15a. Therefore, a diffuser for reducing such flow distortion is used. A structure has been proposed.
  • the flow distortion described above is a state in which the flow velocity distribution and the pressure distribution are non-uniform.
  • the flow passage cross-sectional area of the diffuser passage 15 is changed, or A structure and a method using a circulation passage are employed.
  • the emphasis is on reducing the distortion that occurs on the inlet side (impeller outlet 14 side) of the diffuser passage 15.
  • Patent Document 1 JP-A-10-176699
  • the conventional diffuser passage 15 generally has a shroud side wall surface 15a and a nove side wall surface 15b, which are a pair of opposing wall surfaces, in a parallel shape.
  • the axial flow width W of the is constant in the circumferential direction.
  • the reverse flow region indicated by arrow A in the figure
  • the flow is separated from the side wall surface 15b near the diffuser outlet 18 and the reverse flow area (arrow in the figure) It was found that it was formed with a mark B). In other words, not the shroud side reverse flow region A but the reverse flow region B is considered to cause surging.
  • the present invention has been made in view of the above circumstances, and its object is to separate the flow from the hub side wall surface downstream of the hub side wall surface in the diffuser passage (near the diffuser outlet). It is to provide a centrifugal compressor having a diffuser structure that is difficult to perform.
  • the present invention employs the following means in order to solve the above problems.
  • the centrifugal compressor according to the present invention is provided with a diffuser passage that restores static pressure by decelerating the airflow discharged from the outer peripheral end force of the impeller rotating in the housing.
  • the hub of the diffuser passage The side wall surface is provided with an inclined region approaching the shroud side at a position downstream of the portion parallel to the normal direction of the impeller outlet cross section.
  • the hub side wall surface of the diffuser passage is provided with an inclined region that approaches the shroud side at a position downstream of the portion parallel to the normal direction of the impeller outlet cross section. Therefore, in the inclined region, the radial velocity in the low speed region generated on the side wall of the hub increases, and the radial velocity distribution in the diffuser passage becomes uniform.
  • the inclined region is, for example, an inclined flat surface, a curved surface or a stepped portion formed on the nove side wall surface, and in this inclined region, the closer to the downstream side wall surface, the closer to the downstream side.
  • the axial wall width of the diffuser passage may be narrowed from the upstream side to the downstream side by inclining the hub side wall surface.
  • a preferred position in the length direction of the diffuser passage where the inclined region is provided is a ratio of 0.3 to 0.3 of the diffuser passage from the diffuser inlet to the diffuser outlet (1) with the base point (0) as a base point. This is the range on the downstream side (exit side) from 0.7.
  • the inclined region provided in the diffuser passage is the hub side wall surface. It is preferable to set so that the maximum amount of protrusion toward the side wall of the shroud is about 1Z3 to 1Z5 of the passage width that is equivalent to the size of the backflow area measured.
  • a preferable inclination angle is a force that is 20 degrees or less with respect to the normal line of the impeller outlet cross section.
  • a more preferable inclination angle is a method of the impeller outlet cross section. It is 2 degrees or more and 10 degrees or less with reference to the line. If the angle of inclination is excessive, the air flow is accelerated again by reducing the passage area, which is not preferable.
  • the hub side wall surface of the diffuser passage is provided with an inclined region that approaches the shroud side at a position downstream of a portion parallel to the normal direction of the impeller outlet cross section. Therefore, in this inclined region, the radial speed of the low speed region generated on the hub side wall surface increases. For this reason, the radial velocity distribution in the diffuser passage is made uniform and local separation is less likely to occur, so that the surge flow rate can be reduced and a wide range operation can be achieved to widen the compressor operating range.
  • the present invention described above is suitable for a wide range of a small centrifugal compressor equipped with a vaneless diffuser, such as an automotive turbocharger that requires a wide compressor operating range.
  • FIG. 1 is a cross-sectional view of a diffuser passage showing a first embodiment of a centrifugal compressor according to the present invention.
  • FIG. 2 is a cross-sectional view showing a first modification of FIG.
  • FIG. 3 is a cross-sectional view showing a second modification of FIG.
  • FIG. 4 is a cross-sectional view of a diffuser passage showing a second embodiment of the centrifugal compressor according to the present invention.
  • FIG. 5A is a cross-sectional view showing the main parts of a centrifugal compressor.
  • FIG. 5B is a cross-sectional view showing a conventional structure of a diffuser passage.
  • the centrifugal compressor 10 includes a diffuser passage 15 that recovers static pressure by decelerating the airflow discharged from the outer peripheral end of the impeller 13 that rotates in the housing 11.
  • the diffuser passage 15 is provided so as to connect between the impeller outlet (diffuser inlet) 14 and the scroll 16, and is formed between a pair of opposing wall surfaces including the shroud side wall surface 15a and the nozzle side wall surface 15b. Has been.
  • FIG. 1 is a cross-sectional view of the diffuser passage 15 showing the first embodiment.
  • This diffuser passage 15 also introduces the air flow (indicated by the white arrow in the figure) from which the outer peripheral end force of the impeller 13 is also discharged into the diffuser inlet 14 force between the shroud side wall surface 15a and the hub side wall surface 15b.
  • the airflow guided to the formed flow path is caused to flow from the diffuser outlet 18 to the scroll 16.
  • the hub side wall surface 15b of the diffuser passage 15 is provided with an inclined plane 20 approaching in the direction of the shroud side wall surface 15a at a position downstream of a portion parallel to the normal direction of the impeller outlet cross section. ing.
  • This inclined plane 20 is an inclined area formed on the hub side wall surface 15b of the diffuser passage 15, and is closer to the shroud side wall surface 15a as it is separated from the diffuser inlet 14 and closer to the diffuser outlet 18, and between the opposing wall surfaces.
  • the axial flow path width W which is the distance, is reduced to Wa.
  • the inclined region formed by the inclined wall surface 20 is upstream of the passage in the diffuser passage 15 in which the flow path length in the normal direction is L and parallel to the normal direction and the flow path length is La. Is inclined toward the shroud side wall surface 15a, and is provided in the downstream portion where the flow path length is Lb.
  • a suitable length of the downstream portion Lb that becomes the inclined region is set to a length La of the upstream portion parallel to the normal direction of 0.3 to 0.7. The remaining part on the downstream side.
  • the inclination angle ⁇ when the inclined region is a plane is preferably set to 20 degrees or less with reference to the normal line of the impeller outlet cross section.
  • the more suitable inclination angle ⁇ is 2 degrees or more and 10 degrees or less with respect to the normal line of the impeller outlet cross section.
  • the above-mentioned normal line and normal direction of the impeller outlet cross section mean a straight line extending in the radial direction from the axial center line 17 around which the impeller 13 rotates through the impeller outlet cross section and its direction. It is similar to the air flow direction.
  • the diffuser passage 15 including the inclined region formed by the inclined wall surface 20 has the shroud side wall surface 15a and the hub side wall surface 15b both parallel to the normal direction and the axial flow path width W.
  • the axial flow path width W is toward the diffuser outlet 18 side due to the upstream region where the is constant and the inclined wall surface 20 where the hub side wall surface 15b is inclined toward the shroud side wall surface 15a. It is narrowed and has an inclined area on the downstream side.
  • the airflow introduced from the diffuser inlet 14 is decelerated by flowing through the diffuser passage 15 to recover the static pressure.At this time, on the downstream side approaching the diffuser outlet 18, it is generated near the wall surface. A low-speed region air flow, which is considered to cause separation from the side wall surface 15b, is gradually guided toward the shroud side wall surface 15a by being guided to the inclined wall surface 20.
  • the low speed region is a region where the velocity component in the radial direction from the diffuser inlet 14 toward the diffuser outlet 18 is low.
  • the radial direction and the normal direction described above coincide.
  • the surge flow rate can be reduced, so that a wide range expansion that extends the operating range of the centrifugal compressor can be achieved.
  • a vane-less diffuser such as an automobile turbocharger
  • the axial flow path width W is conversely narrowed toward the diffuser outlet 18 side.
  • the airflow guided to the inclined wall surface 20 gradually flows toward the hub side wall surface 15b. It is accelerated by following. For this reason, the velocity distribution in the radial direction is force! This increases the speed difference between the speed shroud side wall surface 15a and the hub side wall surface 15b where the low speed region exists, thereby further increasing non-uniformity.
  • an inclined region is formed by an inclined curved surface 21 instead of the inclined plane 20 of FIG.
  • This inclined curved surface 21 is in the length direction of the diffuser passage that provides the inclined region.
  • the preferred position (ratio of length Lb) and the maximum protrusion Wb from the wall side wall surface 15b to the shroud side wall surface 15a are the same as those of the inclined plane 20, and are appropriately curved to satisfy this condition. Etc. may be set.
  • the curved surface may be either a concave curved surface or a convex curved surface as viewed from inside the diffuser passage 15.
  • an inclined region is formed by an inclined folding line 22 instead of the inclined plane 20 of FIG.
  • the inclined fold line 22 is composed of a flat inclined portion 22a and a parallel portion 22b on the diffuser outlet 18 side.
  • the parallel portion 22b is parallel to the shroud side wall surface 15a and the hub side wall surface 15b.
  • the inclined folding line 22 is a suitable position in the length direction of the diffuser passage where the inclined region is provided (the ratio of the length Lb) and the maximum value Wb of the protrusion amount from the side wall wall surface 15b to the shroud side wall surface 15a. Is the same as the inclined plane 20.
  • the inclined folding line 22 shown in the figure may be combined with an inclined portion 22a having a force of two or more steps, which is a combination of the inclined portion 22a and the parallel portion 22b, or may be combined with a curved surface.
  • FIG. 4 is a cross-sectional view showing a second embodiment of the centrifugal compressor according to the present invention.
  • symbol is attached
  • path 30 is divided
  • the hub side wall surface 30b is downstream of the parallel portion 32 that is a portion parallel to the normal direction of the impeller outlet cross section.
  • An inclined region approaching the shroud side is provided at a position on the side. That is, when the hub side wall surface 30b of the shroud-side inclined portion 33 approaches the shroud side, an inclined region having substantially the same function as the inclined plane 20 described above is formed.
  • the hub side wall surface 30b having an inclined plane similar to the inclined plane 20 increases the velocity component in the radial direction in the low speed region generated near the wall surface of the hub side wall surface 30b.
  • the velocity distribution in the radial direction becomes uniform, and local peeling is less likely to occur.
  • the hub side wall surface 15a of the diffuser passage 15 is provided with an inclined region that approaches the shroud side at a position downstream of the portion parallel to the normal direction of the impeller outlet cross section. Therefore, the radial speed in the low speed region generated on the hub side wall surface 15a increases, and the radial speed distribution in the diffuser passage 15 becomes uniform. Therefore, in the vicinity of the diffuser outlet 18 in the diffuser passage 15, local air flow separation from the wall surface occurs, so that the surge flow can be reduced and a wide range operation that widens the compressor operating range is achieved. it can.

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

Abstract

L'invention concerne un compresseur centrifuge ayant une structure de diffuseur dans laquelle un écoulement de gaz est moins susceptible d'être séparé d'une surface de paroi côté moyeu sur le côté en aval dans un trajet de diffuseur. Le trajet de diffuseur (15) récupère une pression statique par réduction de la vitesse d'un écoulement de gaz déchargé à partir du bord périphérique externe d'une turbine en rotation dans un carter (11). La surface (15b) de paroi côté moyeu du trajet de diffuseur (15) comporte une surface plate inclinée (20) approchant le côté carénage, et la surface inclinée (20) est située à une position sur le côté en aval de cette partie de la surface (15b) de paroi côté moyeu étant parallèle à la direction perpendiculaire à une section transversale d'une sortie de turbine.
PCT/JP2007/052391 2006-09-21 2007-02-09 Compresseur centrifuge WO2008035465A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US11/989,241 US20100129209A1 (en) 2006-09-21 2007-02-09 Centrifugal Compressor
EP07714007A EP2072834A1 (fr) 2006-09-21 2007-02-09 Compresseur centrifuge

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2006255383A JP2008075536A (ja) 2006-09-21 2006-09-21 遠心圧縮機
JP2006-255383 2006-09-21

Publications (1)

Publication Number Publication Date
WO2008035465A1 true WO2008035465A1 (fr) 2008-03-27

Family

ID=39200296

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/JP2007/052391 WO2008035465A1 (fr) 2006-09-21 2007-02-09 Compresseur centrifuge

Country Status (6)

Country Link
US (1) US20100129209A1 (fr)
EP (1) EP2072834A1 (fr)
JP (1) JP2008075536A (fr)
KR (1) KR20080042073A (fr)
CN (1) CN101341341A (fr)
WO (1) WO2008035465A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160317766A1 (en) * 2009-04-29 2016-11-03 Fisher & Paykel Healthcare Limited Fan unit with improved surge characteristics

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP4969433B2 (ja) * 2007-12-19 2012-07-04 三菱重工業株式会社 遠心圧縮機
JP5233436B2 (ja) * 2008-06-23 2013-07-10 株式会社日立プラントテクノロジー 羽根無しディフューザを備えた遠心圧縮機および羽根無しディフューザ
FR2937385B1 (fr) 2008-10-17 2010-12-10 Turbomeca Diffuseur muni d'aubes a orifices
JP5905268B2 (ja) * 2012-01-17 2016-04-20 三菱重工業株式会社 遠心圧縮機
US9303561B2 (en) 2012-06-20 2016-04-05 Ford Global Technologies, Llc Turbocharger compressor noise reduction system and method
US10337529B2 (en) 2012-06-20 2019-07-02 Ford Global Technologies, Llc Turbocharger compressor noise reduction system and method
CN104428538B (zh) * 2012-07-06 2017-07-04 丰田自动车株式会社 内燃机的增压器的压缩机
CN105283674B (zh) * 2013-08-06 2017-08-25 株式会社Ihi 离心压缩机以及增压器
CN105264236B (zh) * 2013-11-22 2018-02-13 株式会社Ihi 离心压缩机及增压器
GB2531029B (en) * 2014-10-07 2020-11-18 Cummins Ltd Compressor and turbocharger
CN104948504A (zh) * 2015-07-10 2015-09-30 南阳新威机电有限公司 一种电气系统及其离心泵
DE102016217446A1 (de) * 2016-09-13 2018-03-15 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung
JP6785946B2 (ja) * 2017-03-28 2020-11-18 三菱重工エンジン＆ターボチャージャ株式会社 遠心圧縮機及びターボチャージャ
DE102017127758A1 (de) * 2017-11-24 2019-05-29 Man Diesel & Turbo Se Radialverdichter und Turbolader
US10851801B2 (en) * 2018-03-02 2020-12-01 Ingersoll-Rand Industrial U.S., Inc. Centrifugal compressor system and diffuser
JP7011502B2 (ja) * 2018-03-20 2022-01-26 本田技研工業株式会社 遠心圧縮機のパイプディフューザ
US11428240B2 (en) * 2018-04-04 2022-08-30 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Centrifugal compressor and turbocharger including the same
US10823195B2 (en) * 2018-04-17 2020-11-03 Pratt & Whitney Canada Corp. Diffuser pipe with non-axisymmetric end wall
CN113785111A (zh) * 2019-06-05 2021-12-10 三菱重工发动机和增压器株式会社 离心压缩机的涡旋构造和离心压缩机
JP2021011828A (ja) * 2019-07-04 2021-02-04 三菱重工業株式会社 多段遠心圧縮機
EP3848590A1 (fr) * 2020-01-07 2021-07-14 ABB Schweiz AG Zone d'écoulement d'un compresseur, compresseur doté d'une telle zone d'écoulement et turbocompresseur doté du compresseur

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS54161007U (fr) * 1978-04-28 1979-11-10
JPH01173426U (fr) * 1988-05-26 1989-12-08
WO1997033092A1 (fr) * 1996-03-06 1997-09-12 Hitachi, Ltd. Compresseur centrifuge et diffuseur pour ce compresseur centrifuge
JPH10176699A (ja) 1996-12-18 1998-06-30 Ishikawajima Harima Heavy Ind Co Ltd 遠心圧縮機
JPH11257291A (ja) * 1998-03-13 1999-09-21 Ishikawajima Harima Heavy Ind Co Ltd 遠心圧縮機のディフューザー

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2967013A (en) * 1954-10-18 1961-01-03 Garrett Corp Diffuser
JPS5520607U (fr) * 1978-07-26 1980-02-08

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS54161007U (fr) * 1978-04-28 1979-11-10
JPH01173426U (fr) * 1988-05-26 1989-12-08
WO1997033092A1 (fr) * 1996-03-06 1997-09-12 Hitachi, Ltd. Compresseur centrifuge et diffuseur pour ce compresseur centrifuge
JPH10176699A (ja) 1996-12-18 1998-06-30 Ishikawajima Harima Heavy Ind Co Ltd 遠心圧縮機
JPH11257291A (ja) * 1998-03-13 1999-09-21 Ishikawajima Harima Heavy Ind Co Ltd 遠心圧縮機のディフューザー

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160317766A1 (en) * 2009-04-29 2016-11-03 Fisher & Paykel Healthcare Limited Fan unit with improved surge characteristics
US10898663B2 (en) * 2009-04-29 2021-01-26 Fisher & Paykel Healthcare Limited Fan unit with improved surge characteristics
US11623056B2 (en) 2009-04-29 2023-04-11 Fisher & Paykel Healthcare Limited Fan unit with improved surge characteristics

Also Published As

Publication number Publication date
KR20080042073A (ko) 2008-05-14
JP2008075536A (ja) 2008-04-03
EP2072834A1 (fr) 2009-06-24
US20100129209A1 (en) 2010-05-27
CN101341341A (zh) 2009-01-07

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