EP0446900A1 - Compresseur à écoulement mixte - Google Patents

Compresseur à écoulement mixte Download PDF

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Publication number
EP0446900A1
EP0446900A1 EP91103850A EP91103850A EP0446900A1 EP 0446900 A1 EP0446900 A1 EP 0446900A1 EP 91103850 A EP91103850 A EP 91103850A EP 91103850 A EP91103850 A EP 91103850A EP 0446900 A1 EP0446900 A1 EP 0446900A1
Authority
EP
European Patent Office
Prior art keywords
flow
mixed
turbine
diffuser
outlet
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.)
Granted
Application number
EP91103850A
Other languages
German (de)
English (en)
Other versions
EP0446900B1 (fr
Inventor
Hideo Nishida
Hiromi Kobayashi
Haruo Miura
Takeo Takagi
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.)
Hitachi Ltd
Original Assignee
Hitachi 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 Hitachi Ltd filed Critical Hitachi Ltd
Publication of EP0446900A1 publication Critical patent/EP0446900A1/fr
Application granted granted Critical
Publication of EP0446900B1 publication Critical patent/EP0446900B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/06—Helico-centrifugal 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
    • F04D29/444—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/62—Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps
    • F04D29/624—Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps 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
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/52—Outlet

Definitions

  • the present invention relates to a mixed-flow compressor, and more particularly to a mixed-flow compressor suitable for enhancement of its performance and for compactness in size.
  • a oblique or mixed flow diffuser in which a flow-out direction is slanted from the radial direction
  • the guide vanes are arranged on a core plate side.
  • a diffuser is provided in the radial direction, but there is no guide vanes.
  • a mixed-flow turbine in which the outlet of the turbine is slanted from the radial direction is used.
  • the curvature of a meridional plane flow path in a meridional plane i.e., a cross section passing through the rotary shaft and vertical to the paper surface
  • a meridional plane flow path is decreased, so that the flow may be kept substantially uniform in the widthwise direction at the outlet of the turbine, i.e., at the inlet of the diffuser. It is thus possible to prevent the generation of the flow deflected toward the core plate.
  • the flow having a volute component is introduced into the mixed-flow diffuser, the flow is deflected to the side plate from the intermediate portion to the outlet portion of the diffuser due to the curvature of right angle with respect to the flow path.
  • a reverse flow will be generated on the core plate side to largely increase the diffuser loss.
  • the length in the axial direction is increased to make the compressor large in size and to increase the friction loss in the flow path.
  • guide vanes each having a height corresponding 10 to 50% of the width of the meridional plane flow path are provided on the core plate side of the diffuser.
  • this could not sufficiently attain the object.
  • problems such as the increase in friction loss and a reduction in safety limit speed.
  • an object of the present invention is to provide an oblique flow compressor that is small in size and ensures a high performance.
  • a mixed-flow compressor in which the outlet portion of the mixed-flow turbine, i.e., the diffuser is curved in the vicinity of the inlet portion of the diffuser, and guide vanes each having a height such that the inlet and outlet vane angles are substantially equal to the average flow angle of design at the outlet of the turbine are provided in the form of a circular wing row at the curved portion on the flow path surface on the side plate side of the diffuser.
  • the diffuser flow path is curved in the radial direction just after the outlet of the turbine, and the guide vanes each having a height such that the inlet and outlet vane angles are substantially equal to the average flow angle of design of the turbine outlet are provided in the form of the circular wing row just after the inlet of the flow pat surface of the diffuser on the side plate side.
  • the guide vanes each having a certain height are provided at the curved portion on the flow path surface of the diffuser plate on the side of the side plate curved in the radial direction in the vicinity of the outlet of the mixed-flow turbine, and the inlet and outlet angles are equal to the average flow angle of the design point at the outlet of the turbine, the flow on the side of the side plate of the mixed-flow turbine outlet is introduced with almost no collision into the guide vanes. Then, since the fluid introduced into the guide vanes is forcibly led, the fluid will flow without separating away from the wall surface of the side plate and will reach the guide vane outlet portion.
  • the flow angle of the fluid led by the guide vane is equal to the flow angle of the portion where guide vanes are not provided. Also, since at the end of the curved portion, the curvature of the meridional plane flow path is small, the meridional flow speed is also kept substantially uniform in the widthwise direction. After all, the flow may be kept uniform in the widthwise direction.
  • the guide vanes each having a height are provided on the surface of the flow path of the diffuser plate on the side of the side plate curved in the radial direction are provided just after the turbine outlet, and the inlet angle and the outlet angle are equal to the average flow angle of the outlet of the turbine, the fluid of the outlet of the mixed-flow turbine on the side of the side plate is introduced into the guide vanes with almost no collision. Then, since the fluid introduced into the guide vanes is forcibly led by the guide vanes, the fluid will flow without separating from the wall surface of the side plate and will reach the outlet portion of the guide vanes.
  • the vane angle is equal to the average flow angle of the design point
  • the flow angle of the fluid led by the guide vanes is equal to the flow angle at the portion where guide vanes are not provided.
  • the curvature of the meridional plane flow path is small at the outlet of the guide vanes is small so that the meridional plane flow speed is also kept substantially uniform in the widthwise direction. After all, the flow is kept constant in the widthwise direction.
  • Fig. 1 is a longitudinal sectional view showing a mixed-flow compressor in accordance with an embodiment of the invention, in which a mixed-flow turbine 1 having a small curvature in a meridional plane flow path is fixed to a rotary shaft 2 by a nut 3.
  • a pair of diffuser plates 4 and 5 each having a curvature in the vicinity of an outlet of the turbine 1 are provided outside of the turbine 1.
  • the diffuser plates 4 and 5 define a diffuser 6 which has a curvature in the vicinity of the turbine 1.
  • One of the diffuser plates 4 is located on a so-called side plate side, whereas the other of the diffuser plates 5 is located on a core plate side.
  • Guide vanes 7 are arranged in the form of a circular wing row at the curved portion of the flow path surface of the diffuser plate 4. It is preferable that the guide vanes 7 are partially provided in the width-wise direction of the flow path and their height are ranged in 20 to 50% of the flow path width.
  • an inlet vane angle ⁇ 1 and an outlet vane angle ⁇ 2 are equal to an average flow angle at a design point of the outlet of the mixed-flow turbine 1 (i.e., an average value of an angle defined by an absolute velocity of the turbine outlet at the design flow rate point with respect to a tangential direction (circumferential direction)).
  • the height of the guide vanes is in the range of 20 to 50% is that the reverse flow preventing effect would be eliminated at the curved portion below 20% and the incidental loss at the flow rate point outside the design point (i.e., a loss generated due to the difference between the flow angle and the vane angle) is increased to degrade the performance of the compressor above 50%.
  • a minimum inlet radius r a of the guide vanes 7 is larger than an maximum outlet radius r b of the turbine 1.
  • a casing 8 is provided radially outwardly of the diffuser plates 4 and 5 to define an outlet flow path 9.
  • a suction pipe 10 is fixed on a gas suction side of the diffuser plater 4.
  • the gas is pressurized and then sucked into the diffuser 6 from the turbine 1.
  • the gas flow is decelerated within the diffuser 6 and is introduced into the casing 8.
  • the flow angle of the fluid on the side of the diffuser plate 4 at the outlet of the turbine 1 is substantially equal to the average flow angle in the widthwise direction, so that the fluid on the side of the diffuser plate 4 is introduced into the guide vanes 7 with almost no collision. Since the introduced fluid is forcibly guided by the guide vanes 7, the fluid may flow without separating away from the wall surface of the diffuser plate 4 and reach the outlet portion of the guide vanes 7.
  • Fig. 4 shows the specific advantage according to this embodiment and the adiabatic efficiency ratio between a conventional mixed-flow compressor using the diffuser without any radial movement vanes and the compressor according to the present embodiment.
  • Curve F indicates the adiabatic efficiency ratio at each suction flow rate of the conventional mixed-flow compressor
  • curve E indicates the adiabatic efficiency ratio at each suction flow rate of the mixed-flow compressor according to the present embodiment.
  • the reference value is defined by regarding as 1.0 the maximum value of the adiabatic efficiency of the mixed-flow compressor according to the present embodiment. As is apparent from Fig. 4, it is possible to considerably improve the adiabatic efficiency ratio in comparison with the conventional mixed-flow compressor having the diffuser without vanes.
  • the present embodiment since according to the present embodiment, it is possible to prevent the separation of the flow at the curved portion of the diffuser, it is possible to considerably reduce the loss at the curved portion and to make uniform the flow in the widthwise direction at the outlet portion of the guide vanes, thereby largely enhancing the performance of the diffuser after the outlet portion of the guide vanes.
  • the meridional plane flow path of the diffuser since the meridional plane flow path of the diffuser is curved in the radial direction, the length of the flow path may be reduced in comparison with that of the conventional mixed-flow diffuser and the frictional loss may also be reduced. As a result, the performance of the mixed-flow compressor may be largely enhanced in comparison with the conventional compressor.
  • the rotary shaft of the compressor may be shortened, the limit speed of the shaft system may be increased.
  • Fig. 5 is an illustration of the assemblage of the compressor of the embodiment shown in fig. 1.
  • the mixed-flow turbine 1 is fitted with the rotary shaft 2 by moving the turbine in the axial direction as indicated by the arrow A.
  • the turbine 1 is fastened to the rotary shaft 2 by the nut 3.
  • the casing 8 integral with the diffuser plate 4 on which the guide vanes 7 are mounted are moved in the axial direction as indicated by the arrow B and is inserted into a fit portion 12 of the diffuser plate 5 which has been coupled with the rotary shaft 2 through a bearing.
  • the minimum inlet diameter of the guide vanes 7 is larger than the maximum outlet diameter of the turbine 1, it is also advantageously easy to assemble the compressor.
  • Fig. 6 is a longitudinal view showing another embodiment.
  • the diffuser 6 is composed of a pair of diffuser plates 4 and 5 each having a curvature in the meridional plane and guide vanes 7 arranged in the form of a circular wing row at the curved portion on the flow path surface of the diffuser plate 4.
  • the inlet angle and the outlet angle of the guide vanes 7 are substantially equal to an average flow angle at the design point of the outlet of the turbine.
  • the height of the guide vanes 7 is ranged in 20 to 50% of the flow path width. Then, the inlet radius r a of the guide vanes 7 is larger than the outlet maximum radius r b of the turbine 1 and is kept constant in the widthwise direction.
  • the inlet radius of the guide vanes 7 is larger than the maximum outlet radius of the turbine 1 and kept constant in the widthwise direction, it is possible to facilitate the assemblage of the compressor and easier to manufacture the diffuser than the case of Fig. 1.
  • Fig. 7 is a longitudinal sectional view showing still another embodiment.
  • Fig. 8 is a cross-sectional view taken along the line VIII-VIII of Fig. 7.
  • the diffuser 6 is composed of a pair of diffuser plates 4 and 5 each having a curvature in the meridional plane and guide vanes 11 arranged in the form of a circular wing row on the flow path surface of the diffuser plate 4.
  • the guide vanes 11 are provided not only on the curved portion of the flow path surface of the diffuser plate 4 but also on the parallel portion downstream of the curved portion.
  • the inlet and outlet angles are substantially equal to the average flow angle at the design point of the outlet of the turbine 1.
  • the height of the guide vanes 11 is ranged in 20 to 50% of the flow path width.
  • the inlet radius r a of the guide vanes 11 is larger than the outlet maximum radius r b of the turbine 1 and is kept constant in the widthwise direction.
  • the fluid on the side of the diffuser plate 4 at the outlet of the mixed-flow vanes 1 is led without separating away from the guide vanes 11 and reaches the outlet of the curved portion.
  • the flow is made substantially uniform in the widthwise direction.
  • the guide vanes 11 are provided to extend to the parallel portion to thereby keep uniform the flow along the parallel portion, it is also possible to enhance the diffuser performance, i.e., the performance of the mixed-flow compressor in comparison with the case shown in Fig. 1.
  • the axial length of the compressor may be reduced. It is therefore possible to make small the mixed-flow compressor and to enhance the limit speed of the shaft system also in this embodiment.
  • Fig. 9 is a longitudinal sectional view according to still another embodiment.
  • the diffuser 6 is composed of a diffuser plate 5 having a curvature in the meridional plane, a diffuser plate 4 curved in the radial direction immediately after the inlet thereof, and guide vanes 11 arranged in the form of a circular wing row on the flow path surface of the diffuser plate 4.
  • the guide vanes 11 are provided at a section between the inlet and outlet of the diffuser 6.
  • the inlet and outlet angles are substantially the same as the average flow angle at the design point of the outlet of the turbine.
  • the height of the guide vanes 11 is in the range of 20 to 50% of the flow path width.
  • the inlet radius r a of the guide vanes 11 is larger than the outlet maximum radius r b of the turbine 1 and is kept constant in the widthwise direction.
  • inlet radius of the guide vanes 11 is larger than the outlet maximum radius of the turbine 1 and is kept constant in the widthwise direction, it is possible to facilitate the assemblage of the compressor and to simplify the manufacture of the diffuser in comparison with the case of Fig. 1.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP91103850A 1990-03-14 1991-03-13 Compresseur à écoulement mixte Expired - Lifetime EP0446900B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP60973/90 1990-03-14
JP2060973A JPH07103874B2 (ja) 1990-03-14 1990-03-14 斜流圧縮機

Publications (2)

Publication Number Publication Date
EP0446900A1 true EP0446900A1 (fr) 1991-09-18
EP0446900B1 EP0446900B1 (fr) 1994-12-28

Family

ID=13157878

Family Applications (1)

Application Number Title Priority Date Filing Date
EP91103850A Expired - Lifetime EP0446900B1 (fr) 1990-03-14 1991-03-13 Compresseur à écoulement mixte

Country Status (3)

Country Link
EP (1) EP0446900B1 (fr)
JP (1) JPH07103874B2 (fr)
DE (1) DE69106179T2 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0610051A1 (fr) * 1993-02-03 1994-08-10 Dresser-Rand Company Diffuseur avec des nervures
EP0908631A2 (fr) * 1997-10-09 1999-04-14 Ebara Corporation Turbomachines
CN1069742C (zh) * 1994-03-18 2001-08-15 株式会社日立制作所 离心式压缩机
ITUA20164221A1 (it) * 2016-06-09 2017-12-09 Fieni Giovanni S R L Gruppo di ventilazione per atomizzazione ed irrorazione
EP3760876A1 (fr) 2019-07-04 2021-01-06 Siemens Aktiengesellschaft Diffuseur pour une turbomachine
EP3805572A1 (fr) 2019-10-07 2021-04-14 Siemens Aktiengesellschaft Diffuseur, turbocompresseur radial

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008017121A1 (de) * 2008-04-02 2009-10-08 Behr Gmbh & Co. Kg Gebläsegehäuse
JP5905268B2 (ja) * 2012-01-17 2016-04-20 三菱重工業株式会社 遠心圧縮機
EP2871369B1 (fr) * 2012-07-06 2019-01-09 Toyota Jidosha Kabushiki Kaisha Compresseur pour compresseur d'alimentation de moteur à combustion interne
ITCO20130037A1 (it) * 2013-09-12 2015-03-13 Internat Consortium For Advanc Ed Design Girante resistente al liquido per compressori centrifughi/liquid tolerant impeller for centrifugal compressors
DE102016108762A1 (de) 2016-05-12 2017-11-16 Man Diesel & Turbo Se Radialverdichter
JP2021124046A (ja) * 2020-02-04 2021-08-30 三菱重工業株式会社 遠心圧縮機のディフューザ構造及び遠心圧縮機

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB693727A (en) * 1950-01-25 1953-07-08 Power Jets Res & Dev Ltd Improvements relating to bladed rotary fluid-flow machines
EP0201912A2 (fr) * 1985-05-15 1986-11-20 Dresser Industries Inc. Diffuseur pour compresseur centrifuge ou similaire
US4850795A (en) * 1988-02-08 1989-07-25 Dresser-Rand Company Diffuser having ribbed vanes followed by full vanes
US4900225A (en) * 1989-03-08 1990-02-13 Union Carbide Corporation Centrifugal compressor having hybrid diffuser and excess area diffusing volute

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS53123607U (fr) * 1977-03-09 1978-10-02
JPS608359B2 (ja) * 1979-08-01 1985-03-02 株式会社日立製作所 遠心圧縮機のディフュ−ザ
JPH0658116B2 (ja) * 1986-08-06 1994-08-03 松下電器産業株式会社 送風装置

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB693727A (en) * 1950-01-25 1953-07-08 Power Jets Res & Dev Ltd Improvements relating to bladed rotary fluid-flow machines
EP0201912A2 (fr) * 1985-05-15 1986-11-20 Dresser Industries Inc. Diffuseur pour compresseur centrifuge ou similaire
US4850795A (en) * 1988-02-08 1989-07-25 Dresser-Rand Company Diffuser having ribbed vanes followed by full vanes
US4900225A (en) * 1989-03-08 1990-02-13 Union Carbide Corporation Centrifugal compressor having hybrid diffuser and excess area diffusing volute

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
COMPRESSED AIR MAGAZINE,Vol.9,September 1985 Washington,USA. "The X-Flo Compressor-A Machine Whose Time Has Come." Page 30-34.*the whole document *
PATENT ABSTRACTS OF JAPAN vol. 5, no. 80 (M-70)(752) 26 May 1981, & JP-A-56 29099 (HITACHI) 23 March 1981, *

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0610051A1 (fr) * 1993-02-03 1994-08-10 Dresser-Rand Company Diffuseur avec des nervures
CN1069742C (zh) * 1994-03-18 2001-08-15 株式会社日立制作所 离心式压缩机
EP0908631A2 (fr) * 1997-10-09 1999-04-14 Ebara Corporation Turbomachines
EP0908631A3 (fr) * 1997-10-09 2000-01-12 Ebara Corporation Turbomachines
US6155779A (en) * 1997-10-09 2000-12-05 Ebara Corporation Turbomachinery
ITUA20164221A1 (it) * 2016-06-09 2017-12-09 Fieni Giovanni S R L Gruppo di ventilazione per atomizzazione ed irrorazione
EP3760876A1 (fr) 2019-07-04 2021-01-06 Siemens Aktiengesellschaft Diffuseur pour une turbomachine
EP3805572A1 (fr) 2019-10-07 2021-04-14 Siemens Aktiengesellschaft Diffuseur, turbocompresseur radial

Also Published As

Publication number Publication date
EP0446900B1 (fr) 1994-12-28
JPH07103874B2 (ja) 1995-11-08
DE69106179T2 (de) 1995-07-27
JPH03264796A (ja) 1991-11-26
DE69106179D1 (de) 1995-02-09

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