US20100129209A1 - Centrifugal Compressor - Google Patents

Centrifugal Compressor Download PDF

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Publication number
US20100129209A1
US20100129209A1 US11/989,241 US98924107A US2010129209A1 US 20100129209 A1 US20100129209 A1 US 20100129209A1 US 98924107 A US98924107 A US 98924107A US 2010129209 A1 US2010129209 A1 US 2010129209A1
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US
United States
Prior art keywords
wall surface
diffuser
side wall
passage
area
Prior art date
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Abandoned
Application number
US11/989,241
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English (en)
Inventor
Koichi Sugimoto
Takashi Shiraishi
Hirotaka Higashimori
Hideyoshi Isobe
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.)
Mitsubishi Heavy Industries Ltd
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
Assigned to MITSUBISHI HEAVY INDUSTRIES, LTD. reassignment MITSUBISHI HEAVY INDUSTRIES, LTD. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: HIGASHIMORI, HIROTAKA, ISOBE, HIDEYOSHI, SHIRAISHI, TAKASHI, SUGIMOTO, KOICHI
Publication of US20100129209A1 publication Critical patent/US20100129209A1/en
Abandoned legal-status Critical Current

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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
    • F04D29/403—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 of a turbo charger or the like.
  • centrifugal compressor of a turbo charger or the like to be used for an internal combustion engine of a motor vehicle for example is commonly known.
  • FIG. 5A is a sectional view showing a relevant section of a conventional centrifugal compressor.
  • a centrifugal compressor 10 shown in the drawing compresses fluid such as gas and air introduced from outside a housing 11 , by rotating an impeller 13 having a large number of blades 12 within the housing 11 .
  • the fluid flow (airflow) formed in this way travels through an impeller exit (Hereunder, also referred to as “diffuser entry”) 14 , being an outer circumferential end of the impeller 13 , then through a diffuser passage 15 and a scroll 16 , and is then delivered to the outside.
  • Reference symbol 17 in the drawing denotes a shaft axis about which the impeller 13 rotates.
  • the diffuser passage 15 mentioned above is provided in between the impeller exit 14 and the scroll 16 , being a passage for recovering static pressure by slowing down the airflow discharged from the impeller 14 .
  • the diffuser passage 15 is normally formed from a pair of opposing wall surfaces. In the description below, one of the pair of the opposing wall surfaces is called a shroud side wall surface 15 a and the other is called a hub side wall surface 15 b.
  • vaneless diffuser In a turbo charger of a motor vehicle to be used in combination with an internal combustion engine, since a wide compressor operation range is required, a type of diffuser that does not have vanes (vaneless diffuser) is normally employed.
  • the distortion in the flow mentioned above refers to the flow velocity distribution or pressure distribution being in a non-uniform state.
  • Conventional techniques for making this uniform employ a structure or method that changes a flow passage sectional area of the diffuser passage 15 , or that utilizes a circulation passage or the like. Each of such conventional techniques has a focus on reducing distortion that occurs on the entry side (impeller exit 14 side) of the diffuser passage 15 .
  • Patent Document 1 Japanese Unexamined Patent Application, Publication No. Hei 10-176699
  • the conventional diffuser passage 15 generally has a shape in which a pair of opposing wall surfaces, namely a shroud side wall surface 15 a and a hub side wall surface 15 b , are in a parallel form, so that an axial direction flow passage width W of the diffuser passage 15 is constant in the circumferential direction.
  • an object of the present invention is to provide a centrifugal compressor having a diffuser structure in which airflow is unlikely to separate from a hub side wall surface on the hub side wall surface downstream side within the diffuser passage (in the vicinity of the diffuser exit).
  • the present invention employs the following means to solve the above problems.
  • a centrifugal compressor according to the present invention is a centrifugal compressor provided with a diffuser passage for recovering static pressure by slowing down discharged air from an outer circumferential end of an impeller that rotates within a housing, wherein a hub side wall surface of the diffuser passage is provided with an inclined area that approaches toward a shroud side, in a position on a downstream side of a portion parallel with a normal line direction of a section surface of an impeller exit.
  • the hub side wall surface of the diffuser passage is provided with the inclined area that approaches the shroud side, in the position on the downstream side of the portion parallel with the normal line direction of the section surface of the impeller exit, the radial direction velocity of the low velocity area that occurs on the hub side wall surface increases in the inclined area, and the radial direction velocity distribution within the diffuser passage is made uniform.
  • the inclined area in this case is a portion of an inclined plane, a curved surface, or a stepped plane, formed on the hub side wall surface for example, and must be such that, in this inclined area, the axial direction flow passage width of the diffuser passage narrows down from the upstream side toward the downstream side by inclining the hub side wall surface so as to approach toward the opposed shroud side wall surface as it approaches the downstream side.
  • a preferable position in the diffuser passage length direction for providing the inclined area, in the diffuser passage in a range between the diffuser entry taken as a base point (0) and the diffuser exit (1) is within a range on the downstream side (exit side) having a ratio of 0.3 to 0.7.
  • the inclined area provided in the diffuser passage be such that the maximum value of an amount of projection from the hub side wall surface toward the shroud side wall surface is set to approximately 1 ⁇ 3 to 1 ⁇ 5 of the passage width, being equivalent to the size of the measured backflow area.
  • the preferable inclination angle is less than or equal to 20 degrees based on the normal line of the impeller exit section when the inclined area is taken as a plane.
  • a more preferable inclination angle is between 2 degrees and 10 degrees, inclusive, based on the normal line of the impeller exit section.
  • An excessively large inclination angle is not preferable, as the airflow is re-accelerated due to the reduction in the passage area in this case.
  • the radial direction velocity of a low velocity area that occurs on the hub side wall surface increases in this inclined area. Therefore, the radial direction velocity distribution within the diffuser passage is made uniform, and separation of the airflow is unlikely to occur locally, so that the surge flow rate can be reduced and the compressor operation range can be widened.
  • the present invention described above is suited for widening the operation range of a small centrifugal compressor provided with a vaneless diffuser, such as a turbo charger for a motor vehicle, which requires a particularly wide compressor operation range.
  • FIG. 1 is a sectional view of a diffuser passage showing a first embodiment of a centrifugal compressor according to the present invention.
  • FIG. 2 is a sectional view showing a first modified example of FIG. 1 .
  • FIG. 3 is a sectional view showing a second modified example of FIG. 1 .
  • FIG. 4 is a sectional view of a diffuser passage showing a second embodiment of a centrifugal compressor according to the present invention.
  • FIG. 5A is a sectional view showing a relevant section of the centrifugal compressor.
  • FIG. 5B is a sectional view showing a conventional structure of a diffuser passage.
  • a centrifugal compressor 10 is provided with a diffuser passage 15 that recovers static pressure by reducing the velocity of a discharged air from an outer circumferential end of an impeller 13 that rotates within a housing 11 .
  • the diffuser passage 15 is provided so as to connect between an impeller exit (diffuser entry) 14 and a scroll 16 , and is formed in between a pair of opposing wall surfaces that comprise a shroud side wall surface 15 a and a hub side wall surface 15 b.
  • FIG. 1 is a sectional view of the diffuser passage 15 showing a first embodiment.
  • This diffuser passage 15 introduces from the diffuser entry 14 , the discharged air (indicated with white arrows in the drawing) from the outer circumferential end of the impeller 13 , and allows the airflow guided to the passage between the shroud side wall surface 15 a and the hub side wall surface 15 b to flow out from a diffuser exit 18 into the scroll 16 .
  • the hub side wall surface 15 b of the diffuser passage 15 is provided with an inclined plane 20 that approaches the direction of the shroud side wall surface 15 a in a position on the downstream side in a portion parallel with a normal line of the section of the impeller exit.
  • This inclined plane 20 is an inclined area, formed on the hub side wall surface 15 b of the diffuser passage 15 , that becomes closer to the shroud side wall surface 15 a as the distance from the diffuser entry 14 increases, approaching the diffuser exit 18 and narrowing an axial direction flow passage width W, which is a distance between the opposing wall surfaces, down to Wa.
  • the inclined area formed by the inclined wall surface 20 inclines toward the direction of the shroud side wall surface 15 a from the upstream side of a passage of a flow passage length La parallel with the normal line direction, and is provided in a downstream portion of flow passage length Lb.
  • the preferred length of the downstream portion Lb, which becomes the inclined area is a portion remaining on the downstream side where the length La of the upstream portion parallel with normal line direction is 0.3 to 0.7.
  • the inclined area provided in the diffuser passage 15 be such that a projection amount of the inclined wall surface from the hub side wall surface 15 b to the shroud side wall surface 15 a is set to be approximately 1 ⁇ 3 to 1 ⁇ 5 of the passage width at the diffuser exit 18 , where the projection amount of the inclined wall surface 20 reaches its maximum value Wb. That is to say, since the maximum value Wb of the projection amount is 1 ⁇ 3 to 1 ⁇ 5W (Wb ⁇ 1 ⁇ 3 to 1 ⁇ 5W), the axial direction flow passage width Wa narrowed by the inclined wall surface 20 is set to be approximately 2 ⁇ 3 to 4 ⁇ 5 of the axial direction flow passage width W (Wa ⁇ 2 ⁇ 3 to 4 ⁇ 5W).
  • the angle of inclination ⁇ where the inclined area is a plane surface is preferably set less than or equal to 20 degrees based on the normal line of the impeller exit section.
  • a further preferable angle of inclination ⁇ is greater than or equal to 2 degrees and less than or equal to 10 degrees based on the normal line of the impeller exit section.
  • the normal line and normal line direction of the impeller exit section mentioned above refers to a straight line or direction that extends radially outward from an axial center line 17 of rotation of the impeller 13 and passes the impeller exit section, and it practically approximates the airflow direction.
  • the diffuser passage 15 provided with the inclined area formed by the inclined wall surface 20 is provided with: an upstream side area where the shroud side wall surface 15 a and the hub side wall surface 15 b are both parallel with the normal line direction and the axial direction flow passage width W is constant; and an inclined area on the downstream side where the axial direction flow passage width W to the diffuser exit 18 side is narrowed by the inclined wall surface 20 , in which the hub side wall surface 15 b inclines toward the shroud side wall surface 15 a.
  • the airflow introduced from the diffuser entry 14 is slowed down by flowing through the diffuser passage 15 , and recovers its static pressure.
  • the airflow in a low velocity area which occurs in the vicinity of the wall surface and is thought to cause the airflow to separate from the hub side wall surface 15 b , is guided to the inclined wall surface 20 so that it gradually flows toward the shroud side wall surface 15 a.
  • the low velocity area in this case is an area where a velocity component in the radial direction from the diffuser entry 14 toward the diffuser exit 18 is low.
  • the radial direction corresponds to the normal line direction.
  • the airflow in the low velocity area that has occurred in the vicinity of the wall surface of the hub side wall surface 15 b increases its velocity component in the radial direction. Therefore, in the diffuser passage 15 , the velocity distribution in the radial direction becomes uniform and flow separation is unlikely to occur locally.
  • the surge flow rate can be reduced, enabling the operation range of the centrifugal compressor to be widened.
  • the invention is applied in the case where a wide range of compressor operation is required from a small sized centrifugal compressor such as a turbo charger provided with a vaneless diffuser, widening of the range can be easily achieved.
  • the axial direction flow passage width W becomes narrower in the opposite direction as it approaches the diffuser exit 18 .
  • the airflow guided to the inclined wall surface 20 is accelerated by gradually flowing toward the hub side wall surface 15 b .
  • an inclined curved surface 21 forms an inclined area.
  • This inclined curved surface 21 is the same as the inclined plane 20 with respect to the preferred position along the diffuser passage length direction in which the inclined area is to be provided (ratio of length Lb), and with respect to the maximum value Wb of the projection amount from the hub side wall surface 15 b toward the shroud side wall surface 15 a , and the curvature may be appropriately set to satisfy these conditions.
  • the curved surface in this case may be either a concave curved surface or convex curved surface when seen from inside the diffuser passage 15 .
  • the surge flow rate can be reduced, and hence the operation range of the centrifugal compressor can be widened and, in particular, if the invention is applied in a case where a wide range of compressor operation is required of a small size centrifugal compressor provided with a vaneless diffuser, the compressor operation range can be easily widened.
  • an inclined inflected line 22 forms an inclined area.
  • This inclined inflected line 22 is formed from a plane inclined section 22 a and a parallel section 22 b on the diffuser exit 18 side, the parallel section 22 b in this case being parallel to the shroud side wall surface 15 a and the hub side wall surface 15 b.
  • this inclined inflected line 22 is the same as the inclined plane 20 with respect to the preferred position along the diffuser passage length direction in which the inclined area is to be provided (ratio of length Lb), and with respect to the maximum value Wb of the projection amount from the hub side wall surface 15 b toward the shroud side wall surface 15 a.
  • the surge flow rate can be reduced, and hence the operation range of the centrifugal compressor can be widened and, in particular, if the invention is applied in a case where a wide range of compressor operation is required of a small size centrifugal compressor provided with a vaneless diffuser, the compressor operation range can be easily widened.
  • the inclined inflected line 22 shown in the drawing is a combination of the inclined section 22 a and the parallel section 22 b .
  • an inclined section 22 a of two or more steps may be combined, and furthermore, a curved surface may also be combined.
  • FIG. 4 is a sectional view showing a second embodiment of the centrifugal compressor according to the present invention.
  • the same reference symbols are given to parts that are the same as in the first embodiment, and detailed descriptions thereof are omitted.
  • a diffuser passage 30 is divided into three areas. Specifically, from the upstream side, a hub side inclined section 31 , a parallel section 32 parallel with the normal line direction of the impeller exit section, and a shroud side inclined section 33 are integrally connected. Therefore, compared to the first embodiment shown in FIG. 1 , the hub side inclined section 31 is added on the most upstream side, and, in the shroud side inclined section 33 , the shroud side wall surface 30 a and the hub side wall surface 30 b are arranged parallel with each other so as to incline toward the shroud side at the same inclination angle.
  • the hub side wall surface 30 b is provided with an inclined area that approaches the shroud side in a position on the downstream side of the parallel section 32 , which is a portion parallel with the normal line of the impeller exit section. That is to say, by having the hub side wall surface 30 b of the shroud side inclined section 33 approach the shroud side, an inclined area having the same effect as that of the inclined plane 20 mentioned above is formed.
  • the surge flow rate can be reduced, and hence the operation range of the centrifugal compressor can be widened and, in particular, if the invention is applied in a case where a wide range of compressor operation is required of a small size centrifugal compressor provided with a vaneless diffuser, the compressor operation range can be easily widened.
  • the radial direction velocity of the low velocity area that occurs on the hub side wall surface 15 a increases, and the radial direction velocity distribution within the diffuser passage 15 is made uniform. Therefore, airflow is unlikely to separate locally from the wall surface in the vicinity of the diffuser exit 18 of the diffuser passage 15 , and hence the surge flow rate can be reduced and the compressor operation range can be widened.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US11/989,241 2006-09-21 2007-02-09 Centrifugal Compressor Abandoned US20100129209A1 (en)

Applications Claiming Priority (3)

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
PCT/JP2007/052391 WO2008035465A1 (fr) 2006-09-21 2007-02-09 Compresseur centrifuge

Publications (1)

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US20100129209A1 true US20100129209A1 (en) 2010-05-27

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US11/989,241 Abandoned US20100129209A1 (en) 2006-09-21 2007-02-09 Centrifugal Compressor

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US (1) US20100129209A1 (ja)
EP (1) EP2072834A1 (ja)
JP (1) JP2008075536A (ja)
KR (1) KR20080042073A (ja)
CN (1) CN101341341A (ja)
WO (1) WO2008035465A1 (ja)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110002780A1 (en) * 2007-12-19 2011-01-06 Mitsubishi Heavy Industries, Ltd. Centrifugal compressor
US20150132120A1 (en) * 2012-07-06 2015-05-14 Toyota Jidosha Kabushiki Kaisha Compressor for supercharger of internal combustion engine
US9303561B2 (en) 2012-06-20 2016-04-05 Ford Global Technologies, Llc Turbocharger compressor noise reduction system and method
US20160097297A1 (en) * 2014-10-07 2016-04-07 Cummins Ltd. Compressor and turbocharger
US20160317766A1 (en) * 2009-04-29 2016-11-03 Fisher & Paykel Healthcare Limited Fan unit with improved surge characteristics
US9874224B2 (en) 2013-11-22 2018-01-23 Ihi Corporation Centrifugal compressor and turbocharger
CN109931295A (zh) * 2017-11-24 2019-06-25 曼恩能源方案有限公司 径向压缩机和涡轮增压器
US10337529B2 (en) 2012-06-20 2019-07-02 Ford Global Technologies, Llc Turbocharger compressor noise reduction system and method
US20190316600A1 (en) * 2018-04-17 2019-10-17 Pratt & Whitney Canada Corp. Diffuser pipe with non-axisymmetric end wall
US20220235794A1 (en) * 2019-06-05 2022-07-28 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Scroll structure of centrifugal compressor and centrifugal compressor
US11408439B2 (en) 2017-03-28 2022-08-09 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Centrifugal compressor and turbocharger
US20230349392A1 (en) * 2020-01-07 2023-11-02 Turbo Systems Switzerland Ltd. Outflow region of a compressor, compressor having an outflow region of said type, and turbocharger having the compressor

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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
EP3032109B1 (en) 2013-08-06 2018-06-13 IHI Corporation Centrifugal compressor and supercharger
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
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
JP2021011828A (ja) * 2019-07-04 2021-02-04 三菱重工業株式会社 多段遠心圧縮機

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US2967013A (en) * 1954-10-18 1961-01-03 Garrett Corp Diffuser
US4315715A (en) * 1978-07-26 1982-02-16 Nissan Motor Company, Limited Diffuser for fluid impelling device
US6203275B1 (en) * 1996-03-06 2001-03-20 Hitachi, Ltd Centrifugal compressor and diffuser for centrifugal compressor

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8425186B2 (en) * 2007-12-19 2013-04-23 Mitsubishi Heavy Industries, Ltd. Centrifugal compressor
US20110002780A1 (en) * 2007-12-19 2011-01-06 Mitsubishi Heavy Industries, Ltd. Centrifugal compressor
US20160317766A1 (en) * 2009-04-29 2016-11-03 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
US10898663B2 (en) * 2009-04-29 2021-01-26 Fisher & Paykel Healthcare Limited Fan unit with improved surge characteristics
US10337529B2 (en) 2012-06-20 2019-07-02 Ford Global Technologies, Llc Turbocharger compressor noise reduction system and method
US9938991B2 (en) 2012-06-20 2018-04-10 Ford Global Technologies, Llc Turbocharger compressor noise reduction system and method
US10415600B2 (en) 2012-06-20 2019-09-17 Ford Global Technologies, Llc Turbocharger compressor noise reduction system and method
US9303561B2 (en) 2012-06-20 2016-04-05 Ford Global Technologies, Llc Turbocharger compressor noise reduction system and method
US10280936B2 (en) * 2012-07-06 2019-05-07 Toyota Jidosha Kabushiki Kaisha Compressor for supercharger of internal combustion engine
US20150132120A1 (en) * 2012-07-06 2015-05-14 Toyota Jidosha Kabushiki Kaisha Compressor for supercharger of internal combustion engine
US9874224B2 (en) 2013-11-22 2018-01-23 Ihi Corporation Centrifugal compressor and turbocharger
US20160097297A1 (en) * 2014-10-07 2016-04-07 Cummins Ltd. Compressor and turbocharger
US11408439B2 (en) 2017-03-28 2022-08-09 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Centrifugal compressor and turbocharger
CN109931295A (zh) * 2017-11-24 2019-06-25 曼恩能源方案有限公司 径向压缩机和涡轮增压器
US20190316600A1 (en) * 2018-04-17 2019-10-17 Pratt & Whitney Canada Corp. Diffuser pipe with non-axisymmetric end wall
US10823195B2 (en) * 2018-04-17 2020-11-03 Pratt & Whitney Canada Corp. Diffuser pipe with non-axisymmetric end wall
US20220235794A1 (en) * 2019-06-05 2022-07-28 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Scroll structure of centrifugal compressor and centrifugal compressor
US11905969B2 (en) * 2019-06-05 2024-02-20 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Scroll structure of centrifugal compressor and centrifugal compressor
US20230349392A1 (en) * 2020-01-07 2023-11-02 Turbo Systems Switzerland Ltd. Outflow region of a compressor, compressor having an outflow region of said type, and turbocharger having the compressor
US11885350B2 (en) * 2020-01-07 2024-01-30 Turbo Systems Switzerland Ltd. Outflow region of a compressor, compressor having an outflow region of said type, and turbocharger having the compressor

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KR20080042073A (ko) 2008-05-14
CN101341341A (zh) 2009-01-07
WO2008035465A1 (fr) 2008-03-27
EP2072834A1 (en) 2009-06-24
JP2008075536A (ja) 2008-04-03

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