US20050163610A1 - Diffuser for centrifugal compressor and method of producing the same - Google Patents

Diffuser for centrifugal compressor and method of producing the same Download PDF

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Publication number
US20050163610A1
US20050163610A1 US10/503,220 US50322004A US2005163610A1 US 20050163610 A1 US20050163610 A1 US 20050163610A1 US 50322004 A US50322004 A US 50322004A US 2005163610 A1 US2005163610 A1 US 2005163610A1
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US
United States
Prior art keywords
diffuser
blade
diffuser blade
centrifugal compressor
suction surface
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.)
Abandoned
Application number
US10/503,220
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English (en)
Inventor
Hirotaka Higashimori
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
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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, HIROSHI, KUMA
Publication of US20050163610A1 publication Critical patent/US20050163610A1/en
Abandoned legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F04D29/444—Bladed diffusers
    • 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 invention relates to a diffuser for a centrifugal compressor and a fabricating method and, in particular, to a diffuser for a centrifugal compressor and a fabricating method capable of reducing both the incidence loss.
  • a centrifugal compressor is well known as a type of compressor for compressing and increasing the pressure of a gas.
  • FIG. 1 is a sectional view of a centrifugal compressor comprising an impeller 12 mounted on a rotary shaft 11 and a casing 13 .
  • the casing 13 has formed therein an impeller accommodating portion, a diffuser portion and a spiral scroll.
  • a blade 14 is mounted on the impeller 12 , and the gas flowing in along the direction of arrow 15 is accelerated by the impeller 12 and flows out along the radial direction 16 of the centrifugal compressor.
  • the diffuser portion on the outer periphery of the impeller 12 includes a diffuser blade 17 for converting the dynamic pressure of the fluid flowing out along the radial direction 16 into a static pressure.
  • the diffuser blade 17 is mounted on an annular disk 18 fitted in the front inner wall of the diffuser portion of the casing 13 , and the diffuser blade 17 extends toward the rear inner wall (along the height) of the diffuser portion in the casing.
  • FIG. 2 is a perspective view of the conventional diffuser comprising a plurality of two-dimensional diffuser blade 17 mounted on the annular disk 18 .
  • the cross section A-A of the diffuser blade 17 is rectangular.
  • the connection between each side wall of the diffuser blade 17 and the annular disk 18 is defined by an arcuate surface, and the curves connecting the center of the radius of curvature of the arcuate surfaces extend smoothly along the diffuser blade 17 and intersect to each other.
  • a ridge line is formed by the intersection of the arcuate surfaces to prevent stalling and surging.
  • This conventional diffuser blade is proposed and disclosed in, for example, Japanese Unexamined Patent Publication No. 10-77997.
  • the gas flowing out of the impeller 12 flows into the diffuser portion in the direction of arrow 20 .
  • the angle between the velocity vector of the gas and an axis tangent to the circumference of the annular disk 18 is referred to as flow angle ⁇ .
  • the distribution of the flow angle ⁇ along the height of the diffuser blade has a parabolic shape wherein the angle is substantially zero at one side where the diffuser blade 17 is mounted to the annular disk 18 (shroud end S) and at the other side rear the inner wall of the casing (hub end H), while the flow angle ⁇ is positive in the intermediate area therebetween.
  • FIG. 3 is a graph showing the distribution of the flow angle along the height of the diffuser blade, in which the abscissa is the height of the diffuser blade and the ordinate is the flow angle ⁇ .
  • Each diffuser blade 17 is mounted obliquely on the annular disk 18 in a direction (length direction) from the impeller of the diffuser mounted portion toward the scroll.
  • the surface impinged by the gas flowing into the diffuser 17 is called a pressure surface, and the surface opposite to the pressure surface a suction surface.
  • the angles of the suction surface and the pressure surface relative to the axis tangent to the circumference of the annular disk 18 are referred to as a suction surface blade angle ⁇ ksuc and a pressure surface blade angle ⁇ kpre , respectively.
  • the suction surface blade angle ⁇ ksuc and the pressure surface blade angle ⁇ kpre are substantially constant over the height of the diffuser blade 17 .
  • the difference ( ⁇ ksuc ) between the flow angle ⁇ and the suction surface blade angle ⁇ ksuc is defined as an incidence In.
  • the incidence In becomes negative near the hub end H and the shroud end S (hatched portions in FIG. 3 ) of the diffuser blade 17 .
  • the boundary layer thickness increases, which results in increase in a loss on the suction surface near the hub end H and the shroud end S of the diffuser blade 17 .
  • the present invention has been achieved in view of the problems described above, and the object thereof is to provide a diffuser for the centrifugal compressor and a fabrication method capable of reducing the pressure loss by suppressing the generation of the boundary layer at the suction surface near the hub end and the shroud end of each diffuser blade.
  • a diffuser for a centrifugal compressor comprising a diffuser blade including a suction surface which is concave toward a pressure surface in a cross section, perpendicular to the flow direction.
  • a diffuser for a centrifugal compressor comprising a diffuser blade including a suction surface which defines an acute angle, in a cross section perpendicular to the flow direction, in relation to at least one of a shroud surface and a hub surface.
  • a diffuser for a centrifugal compressor comprising a diffuser blade including a suction surface which is concave toward a pressure surface in a cross section, perpendicular to the flow direction at least in a throat portion and a portion upstream thereof.
  • a diffuser for a centrifugal compressor comprising a suction surface which defines an acute angle, in a cross section perpendicular to the flow direction at least in a throat portion and a portion upstream thereof, in relation to at least one of a shroud surface and a hub surface.
  • the suction surface is formed into a concave surface at least in the throat portion to suppress the generation of a boundary layer near the shroud surface and the hub surface.
  • a method of fabricating a diffuser for a centrifugal compressor comprising the steps of fabricating a two-dimensional blade; and cutting one of the side surfaces of the blade, fabricated in the preceding step, into a concave shape with a ball end mill.
  • the diffuser blade is fabricated by cutting one side surface of the diffuser blade having a two-dimensional shape with a ball end mill.
  • FIG. 1 is a sectional view of a centrifugal compressor.
  • FIG. 2 is a perspective view of a diffuser conventionally used.
  • FIG. 3 is a graph showing the distribution of the flow angle along the height of the diffuser blade.
  • FIG. 4A is a perspective view of a diffuser blade according to the invention.
  • FIG. 4B is a sectional view of a diffuser blade taken in line I in FIG. 4A .
  • FIG. 4C is a sectional view of a diffuser blade taken in line II in FIG. 4A .
  • FIG. 4D is a sectional view of a diffuser blade taken in line III in FIG. 4A .
  • FIG. 4E is a sectional view of a diffuser blade taken in line IV in FIG. 4A .
  • FIG. 4F is a sectional view of a diffuser blade taken in line V in FIG. 4A .
  • FIG. 5 is a graph showing the distribution of the flow angle along the height of a diffuser blade according to the invention.
  • FIG. 6 is a sectional view of a second diffuser blade used with a diffuser according to the invention.
  • FIG. 7A is a top plan view of a diffuser according to the invention.
  • FIG. 7B is a sectional view of a diffuser blade taken in line B-B in FIG. 7A .
  • FIGS. 8A to 8 C are diagrams showing the steps of fabricating a diffuser blade used with a diffuser according to the invention.
  • FIG. 8D is a sectional view showing the portion indicated by III in FIG. 8C .
  • FIG. 8E is a sectional view showing the portions indicated by II and IV in FIG. 8C .
  • FIG. 8F is a sectional view showing the portions indicated by I and V in FIG. 8C .
  • FIG. 4A is a perspective view of a diffuser blade used in a diffuser according to the invention
  • FIGS. 4B to 4 F are sectional views from the upstream side taken in lines I to V, respectively.
  • a suction surface 401 of a diffuser blade 4 is formed into a concave surface toward an opposite pressure surface 402 .
  • at least one of angle ⁇ H which is defined by the suction surface and inner wall of the casing near a hub end H and angle ⁇ S which is defined by the suction surface and, an annular disk near a shroud end S of the diffuser blade 4 is acute.
  • the suction surface is formed as a concave surface toward the pressure surface.
  • FIG. 5 is a graph showing the distribution of the flow angle along the height of the diffuser blade.
  • FIG. 6 is a sectional view of a second diffuser blade according to the invention, which is configured of not a curved surface but of bent flat surfaces.
  • FIG. 7A is a top plan view of the diffuser according to the invention
  • FIG. 7B a sectional view of the diffuser blade along line B-B in FIG. 7A
  • the constant-pressure curves of the gas between the two diffuser blades 41 , 42 are shown in FIG. 7A .
  • Area between the normal line C-C to the center line along the length of the first diffuser blade 41 from the upstream end of the second diffuser blade 42 and the upstream end of the first diffuser blade 41 is defined as a throat
  • the length from the upstream end of the first diffuser blade 41 to the normal line C-C is defined as a throat length XT.
  • the pressure distribution is in the shape of a fan centered at the upstream end of the second diffuser blade 42 .
  • the pressure in the area “a” connecting the upstream ends of the blade is low, while the pressure in the area “b” connecting the upstream end of the second diffuser blade 42 and the center of the throat area of the first diffuser blade 42 is high.
  • FIG. 7B is a sectional view along line B-B perpendicular to the center line along the length of the first diffuser blade 41 in the throat area.
  • the gas pressure distribution is such that the higher the pressure, the nearer to the first diffuser blade 41 .
  • the gas develops a secondary flow 43 from the suction surface of the first diffuser blade 41 toward the pressure surface of the second diffuser blade 42 .
  • the boundary layer thickness on the suction surface of the first diffuser blade 41 near the hub end H and the shroud end S is reduced while. Therefore the incidence loss is reduced.
  • the constant-pressure curves assume a form perpendicular to the center line along the length of the first diffuser blade 41 and the second diffuser blade 42 . Therefore, the gas is prevented from flowing from the suction surface of the first diffuser blade 41 toward the pressure surface of the second diffuser blade 42 .
  • it is especially important to form a throat and a concave suction surface at upstream of the throat, while the portion downstream of the throat is not required to be formed into a concave shape.
  • FIGS. 8A to 8 F are diagrams for explaining the steps of fabricating a diffuser blade according to this invention.
  • a two-dimensional diffuser blade having a rectangular cross section is fabricated ( FIG. 8A ).
  • the suction surface of the two-dimensional diffuser blade is cut with the ball end mill thereby to form a concave suction surface.
  • a concave suction surface is formed by cutting along the other end ( FIG. 8C ).
  • the angles ⁇ H and ⁇ S that the suction surface forms with the hub surface and the shroud surface, respectively, of the diffuser blade are acute.
  • a two-dimensional diffuser blade has the greatest thickness at the longitudinally central portion thereof, and therefor the cross section of the diffuser blade according to the invention is symmetric longitudinally about the central portion (III) thereof.
  • the cross section of the central portion (III) is shaped as shown in FIG. 8D .
  • the cross sections of the portions (II) and (IV) are shaped as shown in FIG. 8E , and the cross sections of the portions (I) and (V) as shown in FIG. 8F .
  • the embodiment of the invention described above refers to an application of the diffuser according to the invention to a centrifugal compressor. It is apparent, however, that the diffuser according to this invention is also applicable to a centrifugal blower and a centrifugal pump with equal effect.
  • the boundary layer generated on the suction surface near the shroud end and the hub end of the diffuser blade is reduced, whereby the incidence loss is reduced.
  • the diffuser blade can be easily fabricated by cutting a two-dimensional diffuser blade with a ball end mill.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US10/503,220 2002-12-04 2003-12-04 Diffuser for centrifugal compressor and method of producing the same Abandoned US20050163610A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
JP2002-352327 2002-12-04
JP2002352327 2002-12-04
PCT/JP2003/015553 WO2004051091A1 (fr) 2002-12-04 2003-12-04 Diffuseur pour compresseur centrifuge et son procede de production

Publications (1)

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US20050163610A1 true US20050163610A1 (en) 2005-07-28

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US (1) US20050163610A1 (fr)
EP (1) EP1568891A4 (fr)
JP (1) JPWO2004051091A1 (fr)
WO (1) WO2004051091A1 (fr)

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070059170A1 (en) * 2005-09-13 2007-03-15 Ingersoll-Rand Company Diffuser for a centrifugal compressor
FR2958346A1 (fr) * 2010-03-30 2011-10-07 Turbomeca Compresseur de turbomachine
US20170342847A1 (en) * 2016-05-26 2017-11-30 Rolls-Royce Corporation Diffuser having shaped vanes
US20180216629A1 (en) * 2017-01-27 2018-08-02 Man Diesel & Turbo Se Radial Compressor and Turbocharger
US20200166049A1 (en) * 2018-11-27 2020-05-28 Honeywell International Inc. High performance wedge diffusers for compression systems
CN112627980A (zh) * 2020-11-16 2021-04-09 株洲丰发精工实业有限公司 一种用于航空发动机的扩压器及其加工方法
US11098730B2 (en) 2019-04-12 2021-08-24 Rolls-Royce Corporation Deswirler assembly for a centrifugal compressor
US11187243B2 (en) 2015-10-08 2021-11-30 Rolls-Royce Deutschland Ltd & Co Kg Diffusor for a radial compressor, radial compressor and turbo engine with radial compressor
US11261878B2 (en) * 2019-08-22 2022-03-01 Mitsubishi Heavy Industries, Ltd. Vaned diffuser and centrifugal compressor
US11286952B2 (en) 2020-07-14 2022-03-29 Rolls-Royce Corporation Diffusion system configured for use with centrifugal compressor
US11333171B2 (en) * 2018-11-27 2022-05-17 Honeywell International Inc. High performance wedge diffusers for compression systems
US20220216487A1 (en) * 2021-01-07 2022-07-07 Ingineers Solid oxide fuel cell power generation system
US11441516B2 (en) 2020-07-14 2022-09-13 Rolls-Royce North American Technologies Inc. Centrifugal compressor assembly for a gas turbine engine with deswirler having sealing features
US11480183B2 (en) * 2019-11-28 2022-10-25 Ingineers Hermetic blower for high-temperature gas
US11578654B2 (en) 2020-07-29 2023-02-14 Rolls-Royce North American Technologies Inc. Centrifical compressor assembly for a gas turbine engine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP5766595B2 (ja) * 2011-12-15 2015-08-19 三菱重工業株式会社 遠心ターボ機械
JP2017096196A (ja) * 2015-11-26 2017-06-01 三菱重工業株式会社 静止ベーンおよび当該静止ベーンを備えた遠心圧縮機

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2708883A (en) * 1950-03-03 1955-05-24 Escher Wyss Ag Arrangement for use in radial centrifugal compressors and pumps for the conversion of kinetic energy of the flowing medium into pressure energy
US3778186A (en) * 1972-02-25 1973-12-11 Gen Motors Corp Radial diffuser
US3930746A (en) * 1973-06-18 1976-01-06 United Turbine Ab & Co., Kommanditbolag Outlet diffusor for a centrifugal compressor
US4027997A (en) * 1975-12-10 1977-06-07 General Electric Company Diffuser for a centrifugal compressor
US4031809A (en) * 1974-10-14 1977-06-28 Evgenia Isaevna Shraiman Method of machining curvilinear surfaces
US4260304A (en) * 1979-10-10 1981-04-07 Dresser Industries, Inc. Method for machining an impeller cover
US4798518A (en) * 1982-03-09 1989-01-17 Wilhelm Gebhardt Gmbh Fan unit for use with duct systems
US5125775A (en) * 1987-11-20 1992-06-30 Starrfrasmaschinen Ag Method for machining a workpiece by end-face cutting tool
US5733080A (en) * 1993-09-29 1998-03-31 Siemens Aktiengesellschaft Process for milling a turbine-blade profile extending along a main axis
US6077002A (en) * 1998-10-05 2000-06-20 General Electric Company Step milling process

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2419669A (en) * 1942-05-08 1947-04-29 Fed Reserve Bank Diffuser for centrifugal compressors
US3719430A (en) * 1971-08-24 1973-03-06 Gen Electric Diffuser
JPS5771799U (fr) * 1980-10-21 1982-05-01
JP3153409B2 (ja) * 1994-03-18 2001-04-09 株式会社日立製作所 遠心圧縮機の製作方法
WO1999061801A1 (fr) * 1998-05-28 1999-12-02 Ebara Corporation Turbomachine

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2708883A (en) * 1950-03-03 1955-05-24 Escher Wyss Ag Arrangement for use in radial centrifugal compressors and pumps for the conversion of kinetic energy of the flowing medium into pressure energy
US3778186A (en) * 1972-02-25 1973-12-11 Gen Motors Corp Radial diffuser
US3930746A (en) * 1973-06-18 1976-01-06 United Turbine Ab & Co., Kommanditbolag Outlet diffusor for a centrifugal compressor
US4031809A (en) * 1974-10-14 1977-06-28 Evgenia Isaevna Shraiman Method of machining curvilinear surfaces
US4027997A (en) * 1975-12-10 1977-06-07 General Electric Company Diffuser for a centrifugal compressor
US4260304A (en) * 1979-10-10 1981-04-07 Dresser Industries, Inc. Method for machining an impeller cover
US4798518A (en) * 1982-03-09 1989-01-17 Wilhelm Gebhardt Gmbh Fan unit for use with duct systems
US5125775A (en) * 1987-11-20 1992-06-30 Starrfrasmaschinen Ag Method for machining a workpiece by end-face cutting tool
US5733080A (en) * 1993-09-29 1998-03-31 Siemens Aktiengesellschaft Process for milling a turbine-blade profile extending along a main axis
US6077002A (en) * 1998-10-05 2000-06-20 General Electric Company Step milling process

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070059170A1 (en) * 2005-09-13 2007-03-15 Ingersoll-Rand Company Diffuser for a centrifugal compressor
US7581925B2 (en) * 2005-09-13 2009-09-01 Ingersoll-Rand Company Diffuser for a centrifugal compressor
FR2958346A1 (fr) * 2010-03-30 2011-10-07 Turbomeca Compresseur de turbomachine
US11187243B2 (en) 2015-10-08 2021-11-30 Rolls-Royce Deutschland Ltd & Co Kg Diffusor for a radial compressor, radial compressor and turbo engine with radial compressor
US10352237B2 (en) * 2016-05-26 2019-07-16 Rolls-Royce Corporation Diffuser having shaped vanes
US20170342847A1 (en) * 2016-05-26 2017-11-30 Rolls-Royce Corporation Diffuser having shaped vanes
US20180216629A1 (en) * 2017-01-27 2018-08-02 Man Diesel & Turbo Se Radial Compressor and Turbocharger
US20200166049A1 (en) * 2018-11-27 2020-05-28 Honeywell International Inc. High performance wedge diffusers for compression systems
US10871170B2 (en) * 2018-11-27 2020-12-22 Honeywell International Inc. High performance wedge diffusers for compression systems
US11333171B2 (en) * 2018-11-27 2022-05-17 Honeywell International Inc. High performance wedge diffusers for compression systems
US11098730B2 (en) 2019-04-12 2021-08-24 Rolls-Royce Corporation Deswirler assembly for a centrifugal compressor
US11261878B2 (en) * 2019-08-22 2022-03-01 Mitsubishi Heavy Industries, Ltd. Vaned diffuser and centrifugal compressor
US11480183B2 (en) * 2019-11-28 2022-10-25 Ingineers Hermetic blower for high-temperature gas
US11286952B2 (en) 2020-07-14 2022-03-29 Rolls-Royce Corporation Diffusion system configured for use with centrifugal compressor
US11815047B2 (en) 2020-07-14 2023-11-14 Rolls-Royce North American Technologies Inc. Centrifugal compressor assembly for a gas turbine engine with deswirler having sealing features
US11441516B2 (en) 2020-07-14 2022-09-13 Rolls-Royce North American Technologies Inc. Centrifugal compressor assembly for a gas turbine engine with deswirler having sealing features
US11578654B2 (en) 2020-07-29 2023-02-14 Rolls-Royce North American Technologies Inc. Centrifical compressor assembly for a gas turbine engine
CN112627980A (zh) * 2020-11-16 2021-04-09 株洲丰发精工实业有限公司 一种用于航空发动机的扩压器及其加工方法
US11764372B2 (en) * 2021-01-07 2023-09-19 Ingineers Solid oxide fuel cell power generation system
US20220216487A1 (en) * 2021-01-07 2022-07-07 Ingineers Solid oxide fuel cell power generation system

Also Published As

Publication number Publication date
JPWO2004051091A1 (ja) 2006-03-30
WO2004051091A1 (fr) 2004-06-17
EP1568891A1 (fr) 2005-08-31
EP1568891A4 (fr) 2006-01-04

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Owner name: MITSUBISHI HEAVY INDUSTRIES, LTD., JAPAN

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