• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    1532965 Cenrifugal compressors DEERE & CO 1 Dec 1975 [4 Dec 1974] 49203/75 Heading F1C A diffuser for use with a centrifugal compressor rotor comprises diffusion passages 28 of which the longitudinal axis 42 follows an at least approximately logarithmic spiral path which may be approximated to by a circular arc having a centre 50 located on a raduis 58 which is perpendicular to the direction 56 at which gases leave the compressor impeller at the design speed. Adjacent diffusion passages 28 intersect at their radially inner ends to provide a semi-vaneless diffusion space 68 lying within a circle 66. For ease of manufacture, each. diffusion passage 28 may be formed by milling the two halves 14, 16 of the diffuser to afford a cylindrical part 76 radially inwardly of a plane 70 which intersects the circle 66 at the radially inner side 72 of the diffusion passage, a part 78 extending from the plane 70 to a plane 80 and a part 82 extending beyond the plane 80. The parts 78 and 82 have divergence angles of 3 degrees and 6 degrees respectively. A shockwave located near the plane 70 reduces the initially supersonic velocity. (Mach number about 1.5) to a subsonic velocity.
    公开号:SU1194291A3
    申请号:SU752195063
    申请日:1975-12-04
    公开日:1985-11-23
    发明作者:Лаверн Кэссер Мерл；Джесс Вуд Хомер
    申请人:Диир Энд Компани (Фирма)；
    IPC主号:
    专利说明:

    .:: - .. “. BACKGROUND OF THE INVENTION The invention relates to compressed air growth and concerns diffusers of centrifugal compressors. The aim of the invention is to increase the efficiency of the compressor. The drawing shows a centrifugal compressor diffuser. The centrifugal compressor diffuser contains a ring 1 located concentrically with the compressor impeller and having channels 2 located in one plane and bent along a logarithmic spiral, and the cross section of each channel 2 increases from the input 3 to the output 4, and the internal diameter d of ring 1 is not more than 1.047 of the outer diameter of the impeller of the compressor. When the centrifugal compressor operates, the gas enters the diffuser at supersonic speeds, which 12 decreases as the gas passes through channels 2. At the same time, depending on the operating conditions of the compressor, in particular the static pressure value, the primary pressure is at the outlet - secondary shock compression waves, the location of which in channels 2 also depends on the operating conditions. Under preferred operating conditions and the inner diameter of the ring 1 of the diffuser, which is no more than 1.047 of the outer diameter of the impeller, the secondary shock wave does not occur, and the primary moves to the input 3 of the channels 2, i.e. an early shock wave is triggered, which is used to increase pressure reuse and increase compressor efficiency.
    权利要求:
    Claims (1)
    [1]
    DIFFUSER OF A CENTRIFUGAL COMPRESSOR, containing a ring located concentrically to the compressor impeller and having channels located in the same plane and curved along a logarithmic spiral, the cross-sectional area of each channel being made increasing from input to output, characterized in that, in order to increase the efficiency, the inner diameter of the ring 'is not more than 1,047 of the outer diameter of the impeller of the compressor.
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    类似技术:
    公开号 | 公开日 | 专利标题
    SU1194291A3|1985-11-23|Centrifugal compressor diffuser
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    US4923371A|1990-05-08|Wall having cooling passage
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    US3719430A|1973-03-06|Diffuser
    US3861826A|1975-01-21|Cascade diffuser having thin, straight vanes
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    GB645258A|1950-10-25|Improvements in or relating to turbines
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    US3942906A|1976-03-09|Side channel ring compressor
    GB753561A|1956-07-25|Axial flow dynamic compressors, and gas turbine power plants utilising such compressors
    GB983945A|1965-02-24|Improvements in gas turbine engine exhaust system
    US4098074A|1978-07-04|Combustor diffuser for turbine type power plant and construction thereof
    US5011375A|1991-04-30|Gas-dynamic pressure-wave machine with reduced noise amplitude
    同族专利:
    公开号 | 公开日
    CA1053202A|1979-04-24|
    DE2552466A1|1976-06-24|
    AR213279A1|1979-01-15|
    IT1052471B|1981-06-20|
    GB1532965A|1978-11-22|
    DE2552466B2|1979-05-10|
    JPS5175206A|1976-06-29|
    US4012166A|1977-03-15|
    ES443181A1|1977-04-16|
    FR2293610A1|1976-07-02|
    YU40270B|1985-12-31|
    SE7513600L|1976-06-08|
    AU8317275A|1977-01-20|
    CH618776A5|1980-08-15|
    DE2552466C3|1980-01-03|
    FR2293610B1|1979-01-19|
    YU304375A|1982-10-31|
    JPS5936119B2|1984-09-01|
    引用文献:
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    RU2588900C2|2010-12-21|2016-07-10|Дженерал Электрик Компани|Supersonic compressor rotor and supersonic compressor unit|NL73824C|1946-01-19|
    US2708883A|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|
    US2819837A|1952-06-19|1958-01-14|Laval Steam Turbine Co|Compressor|
    US3150823A|1962-02-12|1964-09-29|Ass Elect Ind|Diffusers|
    US3778186A|1972-02-25|1973-12-11|Gen Motors Corp|Radial diffuser|
    US3765792A|1972-03-27|1973-10-16|Avco Corp|Channel diffuser with splitter vanes|
    US3905721A|1974-09-03|1975-09-16|Gen Motors Corp|Centrifugal compressor diffuser|US4181467A|1979-01-31|1980-01-01|Miriam N. Campbell|Radially curved axial cross-sections of tips and sides of diffuser vanes|
    US4484860A|1982-05-17|1984-11-27|Donaldson Company, Inc.|Radial tube centrifugal fan|
    PL143757B1|1984-03-27|1988-03-31|Inst Lotnictwa|Ultrasonic channel-type diffuser in particular a radial one|
    US4799861A|1987-10-29|1989-01-24|Warren Pumps, Inc.|Pump|
    JP2852106B2|1990-07-20|1999-01-27|株式会社日立製作所|Vacuum cleaner and electric blower|
    JP2746783B2|1990-10-30|1998-05-06|キャリアコーポレイション|Centrifugal compressor|
    US5266002A|1990-10-30|1993-11-30|Carrier Corporation|Centrifugal compressor with pipe diffuser and collector|
    US5579999A|1993-07-19|1996-12-03|The United States Of America As Represented By The United States National Aeronautics And Space Administration|Shock-free supersonic elliptic nozzles and method of forming same|
    US6123506A|1999-01-20|2000-09-26|Pratt & Whitney Canada Corp.|Diffuser pipe assembly|
    US6471475B1|2000-07-14|2002-10-29|Pratt & Whitney Canada Corp.|Integrated duct diffuser|
    US6540481B2|2001-04-04|2003-04-01|General Electric Company|Diffuser for a centrifugal compressor|
    US7334990B2|2002-01-29|2008-02-26|Ramgen Power Systems, Inc.|Supersonic compressor|
    US20030210980A1|2002-01-29|2003-11-13|Ramgen Power Systems, Inc.|Supersonic compressor|
    US6760971B2|2002-07-15|2004-07-13|Pratt & Whitney Canada Corp.|Method of making a gas turbine engine diffuser|
    US7293955B2|2002-09-26|2007-11-13|Ramgen Power Systrms, Inc.|Supersonic gas compressor|
    US7434400B2|2002-09-26|2008-10-14|Lawlor Shawn P|Gas turbine power plant with supersonic shock compression ramps|
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    WO2010089670A1|2009-02-04|2010-08-12|General Fusion, Inc.|Systems and methods for compressing plasma|
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    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    US05/529,498|US4012166A|1974-12-04|1974-12-04|Supersonic shock wave compressor diffuser with circular arc channels|
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