WO2004051091A1 - 遠心圧縮機用ディフューザ及びその製造方法 - Google Patents
遠心圧縮機用ディフューザ及びその製造方法 Download PDFInfo
- Publication number
- WO2004051091A1 WO2004051091A1 PCT/JP2003/015553 JP0315553W WO2004051091A1 WO 2004051091 A1 WO2004051091 A1 WO 2004051091A1 JP 0315553 W JP0315553 W JP 0315553W WO 2004051091 A1 WO2004051091 A1 WO 2004051091A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- diffuser
- blade
- diffuser blade
- cross
- centrifugal compressor
- Prior art date
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
- 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 method for manufacturing the same, and more particularly, to a diffuser for a centrifugal compressor that can reduce an incidence loss and reduce a deceleration loss at a throat, and a method for manufacturing the same.
- Centrifugal compressors are well known as a type of compressor that compresses and boosts gas.
- FIG. 1 is a cross-sectional view of a centrifugal compressor, which includes an impeller 1 2 attached to a rotating shaft 1 1 and a casing 13. Inside the casing 13 is formed an impeller storage part, a diffuser part and a spiral scroll hole.
- a blade 14 is attached to the impeller 12, and the gas flowing in the direction of the arrow 15 is accelerated by the impeller 12 and flows out in the radial direction 16 of the centrifugal compressor.
- a diffuser blade 17 for converting the dynamic pressure of the fluid flowing out in the radial direction 16 into a negative pressure is disposed in the diffuser portion on the outer periphery of the impeller 1 2. That is, the diffuser blade 17 is mounted on a ring-shaped disk 18 fitted to the front inner wall of the diffuser portion of the casing 13, and the diffuser blade 17 faces the rear inner wall of the diffuser portion in the casing. Distract (in the height direction).
- Fig. 2 is a perspective view of a conventionally used diffuser in which a plurality of blade-shaped two-dimensional diffuser blades 1 7 are attached to an annular disk 1 8. It is. Note that the AA cross section of the Diffuser 17 wing is rectangular. The connecting portion between the diffuser blade 1 7 and the annular disk 1 8 is an arcuate surface, and the curve connecting the centers of the radii of curvature of the arcuate surface is a smooth curve along the diffuser blade 1 7. Diffuser blades that cross the upstream side of the diffuser blade 17 and form a ridgeline at the intersection to prevent stall and further saging are proposed. It is disclosed in Japanese Utility Model Publication No. 10—7 7 9 9 7.
- the gas flowing out of the impeller 12 flows into the diffuser part from the direction of the arrow 20, and the angle formed by the velocity vector of this gas with the axis along the circumference of the annular disk 18 is referred to as the flow angle c.
- the flow angle ⁇ is almost zero on the side of the diffuser blade 17 attached to the annular disk 18 (shroud end S) and the inner wall of the casing rear side (hub end ⁇ ), and is positive in the intermediate region. It has a parabolic height distribution.
- Fig. 3 is a graph showing the distribution of the flow angle in the height direction of the diffuser blade.
- the horizontal axis represents the diffuser blade height
- the vertical axis represents the flow angle ⁇ .
- the diffuser blade 17 is attached to the annular disk 18 at an angle in the direction (length direction) from the impeller at the diffuser installation section to the scroll, but the surface where the gas flowing into the diffuser 17 collides Is called the suction surface, and the back side of the suction surface is called the pressure surface.
- suction side vane angle a ks is the angle between the axis along a circle circumference of the annular disk 1 8 ue and pressure surface vane angle c k P r e, suction side blade angle a k sue and The pressure surface blade angle c kp re is almost constant in the height direction of the differential user blade 17.
- the present invention has been made in view of the above problems, and is for a centrifugal compressor capable of suppressing pressure loss by suppressing generation of a boundary layer of a suction surface in the vicinity of a hub end and a shroud end of a diffuser blade.
- the purpose is to provide a diffuser and its manufacturing method.
- a diffuser for a centrifugal compressor includes a diffuser blade whose suction surface having a cross-sectional shape perpendicular to the fluid flow direction is concave toward the pressure surface.
- a diffuser for a centrifugal compressor according to a second invention includes a suction surface having a cross-sectional shape perpendicular to the fluid flow direction, and a diffuser blade having an acute angle at least one of an angle formed between the shell surface and the hub surface. .
- a diffuser for a centrifugal compressor includes a diffuser blade in which a suction surface having a cross section perpendicular to the flow direction of the slot and the upstream fluid is concave toward the pressure surface. It has.
- a diffuser for a centrifugal compressor includes at least an angle formed by the suction surface having a cross section perpendicular to the flow direction of the fluid and the upstream portion of the slot, and the shroud surface and the hub surface.
- One has a diffuser blade with an acute angle.
- At least the suction surface of the slot portion is formed as a concave surface, and the generation of a boundary layer on the suction surface near the shell end and the hub end is suppressed.
- the fifth method for manufacturing a diffuser for a centrifugal compressor is as follows: a diffuser blade manufacturing stage that manufactures a diffuser blade having a two-dimensional blade shape, and one side surface of the diffuser blade manufactured in the diffuser blade manufacturing stage is ball-bonded. A cutting step of cutting into a concave shape with a domill is provided.
- the diffuser blade is manufactured by cutting one side surface of a two-dimensional blade-shaped diffuser user blade with a ball mill.
- Figure 1 is a cross-sectional view of a centrifugal compressor.
- Figure 2 is a perspective view of a diffuser that has been used far away.
- Figure 3 is a graph showing the distribution of the far flow angle in the height direction of the diffuser blade.
- FIG. 4A is a perspective view of the diffuser wing used in the diffuser according to the present invention.
- FIG. 4B is a cross-sectional view of the diffuser wing taken along line I of FIG. 4A.
- FIG. 4C is a cross-sectional view of the diffuser wing taken along line I I of FIG. 4A.
- FIG. 4D is a cross-sectional view of the diffuser wing taken along line I I I in FIG. 4A.
- FIG. 4E is a cross-sectional view of the diff user wing along the line of sight IV in FIG. 4A.
- FIG. 4F is a cross-sectional view of the diffuser wing taken along line V of FIG. 4A.
- FIG. 5 is a graph showing the distribution of the flow angle in the direction of the diffuser blade height in the present invention.
- FIG. 6 is a sectional view of a second diff user wing used in the diffuser according to the present invention.
- FIG. 7A is a top view of the diffuser according to the present invention.
- FIG. 7B is a cross-sectional view of the diffuser wing taken along line BB in FIG. 7A.
- FIG. 8A to FIG. 8C are diagrams showing the data used in the diffuser according to the present invention. It is the figure which showed the production procedure of the fuser blade.
- FIG. 8D is a cross-sectional view of the portion indicated by III in FIG. 8C.
- FIG. 8E is a cross-sectional view taken along lines II and IV in FIG. 8C.
- FIG. 8F is a cross-sectional view of the portion indicated by I and V in FIG. 8C. Best Mode for Carrying Out the Invention
- FIGS. 4B to 4F are I to V from the upstream side in the length direction of the diffuser blade 40.
- the negative pressure surface 4 0 1 of the diffuser blade 4 is a concave surface that is recessed toward the pressure surface 4 0 2 on the back surface. That is, at least one of the angle ⁇ ⁇ formed between the suction surface and the casing inner wall near the hub end H of the diffuser blade 4 and the angle ⁇ S formed between the suction surface and the annular disk near the shroud end S is sharp. Is formed.
- the suction surface is assumed to be a smooth curved surface.
- FIG. 5 is a dull chart showing the distribution of the flow angle in the height direction of the diffuser blade according to the present invention.
- the suction surface angle a ksuc becomes smaller near the hub end H and the shroud end S of the diffuser user blade 4. It becomes larger at the center of the diffuser blade 4 in the height direction. Accordingly, the diffuser blade incident I n 2 ( aksac -a) used in the diffuser according to the present invention is negative in the vicinity of the hub end H and the shroud end S of the diffuser blade 4.
- the absolute value is smaller than the conventional diffuser blade.
- FIG. 6 shows a second diffuser used in the diffuser according to the present invention.
- FIG. 7A is a top view of the diffuser according to the present invention
- FIG. 7B is a cross-sectional view along line B-B in FIG. 7A.
- FIG. 7A shows the gas isobars of the two diffuser blades 4 1 and 4 2 and the flow path between the blades.
- C—C region from the upstream end of the second diffuser blade 4 2 to the vertical line drawn from the longitudinal center line of the first diffuser blade 4 1 and the upstream end of the first diffuser blade 4 1
- the length from the upstream end of the first diffuser blade 4 1 to the slot C—C is the length from the upstream end of the first diffuser blade 4 1 to the slot XT.
- the fan-shaped pressure distribution is centered on the upstream end of the second diffuser blade 42, and the pressure in the region a connecting the blade upstream end is low.
- a region b connecting the upstream end of the second diffuser blade 4 2 and the center of the first diffuser blade 42 has a high pressure.
- Fig. 7B shows the cross section along the line B-B perpendicular to the longitudinal center line of the first diffuser blade 41 in the slot region. The closer to fuser blade 41, the higher the pressure.
- a secondary flow 4 3 from the suction surface of the first diffuser blade 4 1 to the pressure surface of the second diffuser blade 4 2 is generated in the gas, and the first diffuser blade 4 1
- the boundary layer formed on the suction surface near the hub end H and the shroud end S of the suction surface is made thinner, and the slot from the upstream end of the first diffuser blade 4 1 to the slot C—C Deceleration loss due to pressure information in the rotor area is reduced.
- the isobars are connected to the first diffuser blade 4 1 and the second diffuser blade 41.
- the fuser blade 4 2 Therefore, there is no flow in the gas from the suction surface of the first diffuser blade 4 1 to the pressure surface of the second diffuser blade 4 2. Therefore, it is particularly important to form the slot portion and the suction surface upstream thereof as a concave surface, and the downstream portion of the slot portion need not be formed as a concave surface.
- FIG. 8A to FIG. 8F are explanatory diagrams of the manufacturing procedure of the diffuser blade used in the diffuser according to the present invention.
- a two-dimensional diffuser blade having a rectangular cross section is manufactured (FIG. 8A). .
- the negative pressure surface of the two-dimensional diffuser blade is cut with a ball end mill to form the negative pressure surface as a concave surface.
- the suction surface becomes concave (Fig. 8C)
- the suction surface becomes the hub surface of the diffuser blade and the shell surface.
- the angles ⁇ ⁇ and ⁇ S formed with the plane are acute angles.
- the cross section of the diffuser blade according to the present invention is symmetrical in the length direction with respect to the center portion (I I I). That is, the cross-sectional shape of the central part (III) is as shown in FIG. 8D, and the cross-sectional shapes of the parts ( ⁇ ) and (IV) are as shown in FIG. The cross-sectional shape of V) is as shown in Fig. 8F.
- the diffuser according to the present invention is applied to a centrifugal compressor.
- the diffuser according to the present invention can be applied to a centrifugal blower or a centrifugal pump. is there.
- the boundary layer generated on the suction surface near the shroud end and the hub end of the diffuser blade is thinned, reducing the loss of incidence and reducing the speed loss. Can be reduced It becomes.
- a diffuser blade can be easily manufactured by cutting a diffuser blade having a two-dimensional blade shape with a ball end mill. It becomes possible.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2004556912A JPWO2004051091A1 (ja) | 2002-12-04 | 2003-12-04 | 遠心圧縮機用ディフューザ及びその製造方法 |
EP03777260A EP1568891A4 (en) | 2002-12-04 | 2003-12-04 | DIFFUSER FOR CENTRIFUGAL COMPRESSORS AND MANUFACTURING METHOD THEREFOR |
US10/503,220 US20050163610A1 (en) | 2002-12-04 | 2003-12-04 | Diffuser for centrifugal compressor and method of producing the same |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2002-352327 | 2002-12-04 | ||
JP2002352327 | 2002-12-04 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2004051091A1 true WO2004051091A1 (ja) | 2004-06-17 |
Family
ID=32463224
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/JP2003/015553 WO2004051091A1 (ja) | 2002-12-04 | 2003-12-04 | 遠心圧縮機用ディフューザ及びその製造方法 |
Country Status (4)
Country | Link |
---|---|
US (1) | US20050163610A1 (ja) |
EP (1) | EP1568891A4 (ja) |
JP (1) | JPWO2004051091A1 (ja) |
WO (1) | WO2004051091A1 (ja) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2013124624A (ja) * | 2011-12-15 | 2013-06-24 | Mitsubishi Heavy Ind Ltd | 遠心ターボ機械 |
WO2017090713A1 (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 |
Families Citing this family (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7581925B2 (en) | 2005-09-13 | 2009-09-01 | Ingersoll-Rand Company | Diffuser for a centrifugal compressor |
FR2958346B1 (fr) * | 2010-03-30 | 2012-04-20 | Turbomeca | Compresseur de turbomachine |
DE102015219556A1 (de) | 2015-10-08 | 2017-04-13 | Rolls-Royce Deutschland Ltd & Co Kg | Diffusor für Radialverdichter, Radialverdichter und Turbomaschine mit Radialverdichter |
US10352237B2 (en) * | 2016-05-26 | 2019-07-16 | Rolls-Royce Corporation | Diffuser having shaped vanes |
DE102017101590A1 (de) * | 2017-01-27 | 2018-08-02 | Man Diesel & Turbo Se | Radialverdichter und Turbolader |
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 |
JP2021032106A (ja) * | 2019-08-22 | 2021-03-01 | 三菱重工業株式会社 | ベーンドディフューザ及び遠心圧縮機 |
KR102261509B1 (ko) * | 2019-11-28 | 2021-06-07 | 주식회사 인지니어스 | 고온 기체용 밀폐형 송풍기 |
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 |
US11286952B2 (en) | 2020-07-14 | 2022-03-29 | Rolls-Royce Corporation | Diffusion system configured for use with centrifugal compressor |
US11578654B2 (en) | 2020-07-29 | 2023-02-14 | Rolls-Royce North American Technologies Inc. | Centrifical compressor assembly for a gas turbine engine |
CN112627980B (zh) * | 2020-11-16 | 2023-04-18 | 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 |
KR102372946B1 (ko) * | 2021-01-07 | 2022-03-10 | 주식회사 인지니어스 | 고체산화물 연료전지 발전시스템 |
Citations (1)
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JPS5771799U (ja) * | 1980-10-21 | 1982-05-01 |
Family Cites Families (14)
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US2419669A (en) * | 1942-05-08 | 1947-04-29 | Fed Reserve Bank | Diffuser for centrifugal compressors |
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 |
US3719430A (en) * | 1971-08-24 | 1973-03-06 | Gen Electric | Diffuser |
US3778186A (en) * | 1972-02-25 | 1973-12-11 | Gen Motors Corp | Radial diffuser |
SE382342B (sv) * | 1973-06-18 | 1976-01-26 | United Turbine Ab & Co | Avloppsdiffusor for centrifugalkompressor |
DE2544612C3 (de) * | 1974-10-14 | 1980-04-10 | Leningradskoe Specialnoe Konstruktorskoe Bjuro Tyaschelych I Unikalnych Stankov, Leningrad (Sowjetunion) | Rundfräsverfahren |
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 |
CH673244A5 (ja) * | 1987-11-20 | 1990-02-28 | Starrfraesmaschinen Ag | |
PL313706A1 (en) * | 1993-09-29 | 1996-07-22 | Siemens Ag | Method of milling turbine vane profiles along their main axis |
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 (en) * | 1998-05-28 | 1999-12-02 | Ebara Corporation | Turbomachinery |
US6077002A (en) * | 1998-10-05 | 2000-06-20 | General Electric Company | Step milling process |
-
2003
- 2003-12-04 EP EP03777260A patent/EP1568891A4/en not_active Withdrawn
- 2003-12-04 JP JP2004556912A patent/JPWO2004051091A1/ja active Pending
- 2003-12-04 WO PCT/JP2003/015553 patent/WO2004051091A1/ja not_active Application Discontinuation
- 2003-12-04 US US10/503,220 patent/US20050163610A1/en not_active Abandoned
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS5771799U (ja) * | 1980-10-21 | 1982-05-01 |
Non-Patent Citations (1)
Title |
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See also references of EP1568891A4 * |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2013124624A (ja) * | 2011-12-15 | 2013-06-24 | Mitsubishi Heavy Ind Ltd | 遠心ターボ機械 |
WO2017090713A1 (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 |
Also Published As
Publication number | Publication date |
---|---|
JPWO2004051091A1 (ja) | 2006-03-30 |
EP1568891A1 (en) | 2005-08-31 |
US20050163610A1 (en) | 2005-07-28 |
EP1568891A4 (en) | 2006-01-04 |
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