• 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:
    In an impeller element of a radial inflow gas turbine the shape of the blades and the outer profile of the hub are such as to make the impeller symmetric about two planes, one through the axis of rotation and one normal to it, the impeller thus deviating from the conventional shape of radial inflow gas turbine impellers, which to a considerable degree has been adapted to the theoretical path of the gas.
    公开号:SU886756A3
    申请号:SU772509051
    申请日:1977-08-10
    公开日:1981-11-30
    发明作者:Мовилл Ян
    申请人:за витель V Ян Мовилл (Норвеги )；
    IPC主号:
    专利说明:

    (54) WORKING WHEEL OF CENTER-TRENCHING TURBINE
    The invention relates to power engineering and can be used in centripetal turbines. The closest to the present invention is a centripetal turbine impeller containing blades with inlet and outlet sections, the first of which has one end surface adjacent to the output section and the other is located perpendicular to the axis of the impeller, and the outer diameter of the input section exceeds the outer diameter of the output section 1. However, in the wheel of the said design, the end surface of the entrance y-piece from the outer diameter to the line of its mating with the output section is formed by a single melt oh curve which significantly complicates the technology of manufacturing the impeller and the turbine efficiency decreases. The purpose of the invention is to simplify the manufacturing technology and increase the efficiency of the turbine. This goal is achieved by the fact that the end surface of the inlet section from the outer diameter to the line of its interface with the outlet section is also located perpendicular to the p-axis, but to the axis of the impeller. FIG. 1 shows an impeller, a longitudinal section; in fig. 2 view A in FIG. 1. Centripetal impeller; The turbine Noah contains blades 1 with inlet and outlet sections 2 and 3, the first of which has one end surface 4 mating with the output section 3, and the other one is located perpendicular to the axis of the impeller, and the outer diameter C the inlet section 2 exceeds the outer diameter D | j of the outlet section 3. The end face 4 of the inlet section 2 from the outer diameter D to its interface with the outlet section 3 is also located perpendicular to the axis of the impeller. In operation, the gas enters the inlet section 2, flows between its parallel surfaces and is discharged through the outlet section 3. The proposed constructive implementation of the impeller allows it to be manufactured using simple and productive equipment, and reduced.
    权利要求:
    Claims (1)
    [1]
    Claim
    The impeller of a centripetal turbine, containing blades with inlet and outlet sections, the first of which has one end surface mating with the outlet section, and the other is perpendicular to the axis of the impeller, and the outer diameter of the inlet section exceeds the outer diameter of the outlet section, characterized in that, in order to increase the efficiency and simplify the manufacturing technology, the end surface of the inlet section from the outer diameter e to the interface line with the exit section is also located, perpendicular to the axis of the impeller.
    Sources of information ** taken into account during the examination 1. TKiritsky G.S. Gas turbines of aircraft engines. Oborongiz, 1963, p. 24.
    FIG. 1
    VNIIIPI Order 10612/89
    Circulation 556 Subscription
    Branch of PPP Patent,
    Uzhhorod, Project 4,
    Fie. 2
    类似技术:
    公开号 | 公开日 | 专利标题
    SU886756A3|1981-11-30|Working wheel of centrifugal turbine
    ES486329A1|1980-10-01|Regenerative rotodynamic machines.
    RU2008435C1|1994-02-28|Radial-flow turbine
    US2047501A|1936-07-14|Steam or gas turbine
    US2635849A|1953-04-21|Turbine stage
    US901228A|1908-10-13|Turbo-pump.
    SU1557365A1|1990-04-15|Impeller of centrifugal fan
    US2015059A|1935-09-24|Combustion turbine
    RU2036333C1|1995-05-27|Stator for axial compressor of gas-turbine engine
    US1080743A|1913-12-09|Rotary compressor.
    GB2071765A|1981-09-23|Centrifugal Pump
    US4573870A|1986-03-04|Solid turbine wheel with guided discharge
    SU1196532A1|1985-12-07|Vortex machine
    SU840614A1|1981-06-23|Cooling apparatus
    US3724969A|1973-04-03|Turbine construction
    SU1260535A1|1986-09-30|Vane of vane diffuser unit of centrifugal turbomachine
    SU523197A1|1976-07-30|End stage centrifugal machine
    SU1108220A1|1984-08-15|Axial-radial flow turbomachine action wheel
    SU1353941A1|1987-11-23|Centrifugal pump blade branch
    SU490941A1|1975-11-05|Axial Turbine Stage Guide
    SU1321936A1|1987-07-07|Fan impeller
    SU1132030A1|1984-12-30|Turbine
    SU1339309A1|1987-09-23|Centrifugal compressor diffuser
    SU1206486A1|1986-01-23|Stage of centrifugal low-delivery compressor
    SU1170176A1|1985-07-30|Axial-radial turbomachine closed wheel
    同族专利:
    公开号 | 公开日
    FR2361528A1|1978-03-10|
    DE2734507C2|1985-09-26|
    NO146029B|1982-04-05|
    DE2734507A1|1978-02-16|
    BR7705289A|1978-05-23|
    SE433518B|1984-05-28|
    JPS5321316A|1978-02-27|
    NO146029C|1982-07-14|
    IT1084426B|1985-05-25|
    GB1589774A|1981-05-20|
    NO762794L|1978-02-14|
    FR2361528B1|1983-11-18|
    JPS6056882B2|1985-12-12|
    CA1104498A|1981-07-07|
    US4188169A|1980-02-12|
    SE7709108L|1978-02-12|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    GB848562A|1956-05-17|1960-09-21|Garringtons Ltd|Improvements relating to the construction of gas turbine engines|
    US2975959A|1958-09-30|1961-03-21|Berry W Foster|Back-to-back centrifugal compressor and centripetal turbine having an integral rotordisc|
    FR1236779A|1959-09-24|1960-07-22|Birmingham Small Arms Co Ltd|Profiling of gas turbine blades|
    FR1248048A|1959-10-28|1960-12-09|Paulde Ets|Impeller or blades for pumps or similar machines and machines fitted therewith|
    FR1250210A|1960-03-04|1961-01-06|Birmingham Small Arms Co Ltd|Radial flow blading system|
    GB918674A|1960-04-19|1963-02-13|Garringtons Ltd|Improvements relating to the construction of gas turbine engines|
    ES194629Y|1970-09-05|1975-05-16|I. B. Mei, S. P. A.|SWIVELING PADDLE DEVICE.|
    US3927952A|1972-11-20|1975-12-23|Garrett Corp|Cooled turbine components and method of making the same|
    DE2527498A1|1975-06-20|1976-12-30|Daimler Benz Ag|RADIAL TURBINE WHEEL FOR A GAS TURBINE|US4335997A|1980-01-16|1982-06-22|General Motors Corporation|Stress resistant hybrid radial turbine wheel|
    JPH055356Y2|1989-11-25|1993-02-12|
    US5061154A|1989-12-11|1991-10-29|Allied-Signal Inc.|Radial turbine rotor with improved saddle life|
    US5215439A|1991-01-15|1993-06-01|Northern Research & Engineering Corp.|Arbitrary hub for centrifugal impellers|
    US6511294B1|1999-09-23|2003-01-28|General Electric Company|Reduced-stress compressor blisk flowpath|
    US6524070B1|2000-08-21|2003-02-25|General Electric Company|Method and apparatus for reducing rotor assembly circumferential rim stress|
    US6471474B1|2000-10-20|2002-10-29|General Electric Company|Method and apparatus for reducing rotor assembly circumferential rim stress|
    US6553763B1|2001-08-30|2003-04-29|Caterpillar Inc|Turbocharger including a disk to reduce scalloping inefficiencies|
    US6641361B2|2001-12-12|2003-11-04|Visteon Global Technologies, Inc.|Fuel pump impeller for high flow applications|
    JP3462870B2|2002-01-04|2003-11-05|三菱重工業株式会社|Impeller for radial turbine|
    SE525219C2|2003-05-15|2004-12-28|Volvo Lastvagnar Ab|Turbocharger system for an internal combustion engine where both compressor stages are of radial type with compressor wheels fitted with reverse swept blades|
    US20070231141A1|2006-03-31|2007-10-04|Honeywell International, Inc.|Radial turbine wheel with locally curved trailing edge tip|
    DE102012212896A1|2012-07-24|2014-02-20|Continental Automotive Gmbh|Impeller of an exhaust gas turbocharger|
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    NO762794A|NO146029C|1976-08-11|1976-08-11|IMPELLER ELEMENT IN A RADIAL GAS TURBINE WHEEL|
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