• 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:
    1516762 Centrifugal compressors DEERE & CO 26 Jan 1976 [27 Jan 1975] 02907/76 Heading F1C The rotor of a centrifugal compressor comprises impeller blades 20, some of the blades 20a bearing damper pads 64 on their low-pressure sides for suppressing vibrations in inducer blades 24. The pads may be semi-circular in cross-section and may be integral with blades 20a. The inlet edges 44 of the impeller blades overlap slightly the outlet edges 50 of the inducer blades.
    公开号:SU917709A3
    申请号:SU762316354
    申请日:1976-01-27
    公开日:1982-03-30
    发明作者:Джесс Вуд Хомер
    申请人:Диир Энд Компани (Фирма)；
    IPC主号:
    专利说明:

    one
    The invention relates to construction and can be used in high-speed vane machines, for example, centrifugal compressors.
    A centrifugal impeller of a supercharger, predominantly a centrifugal compressor of a gas turbine gas generator, containing an input axial and output centrifugal rims with curved blades, is known, with damping elements attached to the blades of the centrifugal rim in the area of their inlet edges. axial crown 1.
    However, due to the fact that blades 15
    the axial crown is in contact with the blades of the centrifugal crown throughout the chgane, the pumped gas is not evenly distributed in the centrifugal crown of the wheel, and there is also a tourisation in the meso-blade space, which reduces the efficiency of the wheel.
    The purpose of the invention is to increase efficiency.
    This goal is achieved by the fact that the damping elements are located at 25
    The rear surface of the blades of the centrifugal rim, and the latter in the area of the damping elements are installed relative to the blades of the centrifugal rim under the coal with the formation of variable, increasing from the root to the periphery of the blades.
    In addition, each damping element is made in the form of a half-disk and its lateral surface facing the blade of the axial venia is located parallel to its working surface.
    The angle of divorce of the blades of the crowns is 1-3-,
    FIG. 1 schematically shows an impeller, a slit, in FIG. 2 is a view along arrow A in FIG. 17 in FIG. 3 blade blades in FIG. 4 is a section BB in FIG. 2
    The impeller of a centrifugal supercharger contains an input axial 1 and an output centrifugal 2 vennes with curved blades 3 and 4. At the same time, on the blades 4 of the centrifugal ring 2, in the area of their input edges 5, damping elements 6 are fixed, contacting the blades 3 of the axial, ring 1,
    The damping elements 6 are located on the rear surface 7 of the blades 4 of the centrifugal crown 2, and the latter in the area of the damping elements 6 are installed relative to the blades 3 of the axial crown 1 at an angle d to form a variable gap increasing from the root 8 to the periphery of the 9 blades 3 and 4.
    Each damping element 6 is made in the form of a half disk and its lateral surface U, facing the blade 3 of the axial crown 1, is parallel to its working surface 11. The angle d of the divorce of the blades 3 and 4 of the crowns 1 and 2 is 1-3.
    The damping element 6 can be made either as a separate part, followed by rigidly attaching it to the periphery 9 of the blade 4, or made together with it. When the impeller is operating, the gas passes through the blades 3 and 4 of the axial and centrifugal rims 1 and 2, receiving energy from the injection.
    Through the installation of diffi-element elements, the impeller can withstand resonant oscillations or be introduced into the range of revolutions at which, in nominal cases, the working vanes are destroyed. Mixing the axial crown with respect to the centrifugal crown with a variable gap has the advantage that a ratio of the amount of air in the impeller and a turbulent flow around the centrifugal crown blades 4 are achieved. This improves the efficiency of the impeller. This results in a more uniform air distribution between the individual blades of the impeller or in individual
    aisles which are formed by the blades 4 of the impeller centrifugal rim. Clearances (L increase the number of the centrifugal ring 2 of the impeller flowing from the back side of the blades 4 and result in equalization of the air flow between the blades 4 of the impeller.
    权利要求:
    Claims (3)
    [1]
    1. The impeller of a centrifugal compressor, mainly a centrifugal gas compressor of a gas turbine engine, comprising an axial inlet and an outlet centrifugal rims with curved blades, and on the blades of the centrifugal corona, in the area of their inlet edges, the damping elements are in contact with the axes of the centrifugal rim in the area of the inlet edges attached to the axes of the centrifugal corona in the area of the inlet edges of the axes of the axes of the axis of the vanishing of the axis of the eye, and the wedge, and the axis of the vanes, as well as in the axes of the axes, in the area of their inlet edges are attached to the blades of the centrifugal corona in the area of the inlet edges are fixed damping elements, in contact with the blades of the centrifugal corona in the area of their inlet edges fixed damping elements, in contact with the blades of the axis of the axis of the vanes, as well as in the axis of the axle, and in the axle of the axes. in order to increase efficiency, the damping elements are located on the back surface of the blades of the centrifugal rim, and the latter in the area of the damping elements are set relative axial rim of the blades at an angle with the formation of a variable gap, increasing from the root to the periphery of the shovel
    [2]
    2. A wheel according to claim 1, characterized in that each damping element is made in the form of a half-disk and its side surface facing the blade axial crown is parallel to its working surface.
    [3]
    3. The wheel according to claim 1, which means that the angle of divorce of the shoulder blades is 1-3.
    Sources of information taken into account in the examination
    1, Patent of England No. 586836, cl. F 1 S, 1947.
    L
    1
    类似技术:
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    同族专利:
    公开号 | 公开日
    US3958905A|1976-05-25|
    AR213401A1|1979-01-31|
    DE2602451A1|1976-07-29|
    CA1049986A|1979-03-06|
    CH613753A5|1979-10-15|
    FR2298713A1|1976-08-20|
    IT1059402B|1982-05-31|
    JPS5187609A|1976-07-31|
    SE7600802L|1976-07-28|
    YU39957B|1985-06-30|
    GB1516762A|1978-07-05|
    DE2602451B2|1978-02-16|
    JPS5542275B2|1980-10-29|
    FR2298713B1|1979-07-27|
    AU8317175A|1977-01-20|
    YU18576A|1982-02-28|
    DE2602451C3|1978-10-05|
    ES444613A1|1977-05-01|
    DE2600652A1|1976-07-29|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US1258462A|1915-04-15|1918-03-05|Gen Electric|Centrifugal compressor.|
    GB479427A|1935-05-31|1938-01-31|Gyoergy Jendrassik|Improvements in rotary compressors|
    US2405283A|1941-08-19|1946-08-06|Fed Reserve Bank|Elastic fluid mechanism|
    GB668093A|1949-04-22|1952-03-12|Rolls Royce|Improvements relating to centrifugal compressors|
    US2664240A|1951-03-13|1953-12-29|United Aircraft Corp|Centrifugal compressor rotor vibration damper|
    GB761187A|1953-09-11|1956-11-14|Garrett Corp|Improvements in or relating to bladed wheels for use with elastic fluids|
    US2859933A|1953-09-11|1958-11-11|Garrett Corp|Turbine wheel exducer structure|
    US2941780A|1954-06-17|1960-06-21|Garrett Corp|Elastic fluid turbine and compressor wheels|
    US3627447A|1969-03-17|1971-12-14|United Aircraft Canada|Radial turbines|DE2527498A1|1975-06-20|1976-12-30|Daimler Benz Ag|RADIAL TURBINE WHEEL FOR A GAS TURBINE|
    DE2621201C3|1976-05-13|1979-09-27|Maschinenfabrik Augsburg-Nuernberg Ag, 8900 Augsburg|Impeller for a turbomachine|
    IT1138616B|1980-10-02|1986-09-17|Carrier Corp|CENTRIFUGAL COMPRESSOR|
    FI74115C|1981-03-27|1987-12-10|Foehn Oy|PROPELLER.|
    US4502837A|1982-09-30|1985-03-05|General Electric Company|Multi stage centrifugal impeller|
    US4615659A|1983-10-24|1986-10-07|Sundstrand Corporation|Offset centrifugal compressor|
    US6499953B1|2000-09-29|2002-12-31|Pratt & Whitney Canada Corp.|Dual flow impeller|
    US6589013B2|2001-02-23|2003-07-08|Macro-Micro Devices, Inc.|Fluid flow controller|
    US6607359B2|2001-03-02|2003-08-19|Hood Technology Corporation|Apparatus for passive damping of flexural blade vibration in turbo-machinery|
    US6752594B2|2002-02-07|2004-06-22|The Boeing Company|Split blade frictional damper|
    US6699015B2|2002-02-19|2004-03-02|The Boeing Company|Blades having coolant channels lined with a shape memory alloy and an associated fabrication method|
    JP4007062B2|2002-05-22|2007-11-14|株式会社日立製作所|Gas turbine and gas turbine power generator|
    CA2432831A1|2003-06-20|2004-12-20|Peter G. Mokry|An impeller and a supercharger for an internal combustion engine|
    US7607886B2|2004-05-19|2009-10-27|Delta Electronics, Inc.|Heat-dissipating device|
    US7156612B2|2005-04-05|2007-01-02|Pratt & Whitney Canada Corp.|Spigot arrangement for a split impeller|
    CN100451344C|2005-11-24|2009-01-14|台达电子工业股份有限公司|Centrifugal fan and its fan blade|
    WO2009065894A1|2007-11-20|2009-05-28|Mann+Hummel Gmbh|Compressor wheel of a centrifugal compressor and method for producing said compressor wheel|
    FR2944060B1|2009-04-06|2013-07-19|Turbomeca|SECONDARY AIR SYSTEM FOR CENTRIFUGAL OR MIXED COMPRESSOR|
    US9033670B2|2012-04-11|2015-05-19|Honeywell International Inc.|Axially-split radial turbines and methods for the manufacture thereof|
    CN104806560B|2014-01-23|2017-10-27|珠海格力电器股份有限公司|Obturator and centrifugal compressor|
    US10100841B2|2016-03-21|2018-10-16|General Electric Company|Centrifugal compressor and system|
    DE102016108762A1|2016-05-12|2017-11-16|Man Diesel & Turbo Se|centrifugal compressors|
    CN106401990A|2016-05-30|2017-02-15|西北工业大学|Air compressor with vane wheel having tandem vanes and splitter vanes and tandem vane grid pressure expander|
    CN112360808B|2020-09-22|2021-09-21|东风汽车集团有限公司|A multistage impeller structure and turbo charger for turbo charger|
    CN112360809B|2020-09-22|2021-09-21|东风汽车集团有限公司|Multistage impeller structure for turbocharger|
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    US05/544,520|US3958905A|1975-01-27|1975-01-27|Centrifugal compressor with indexed inducer section and pads for damping vibrations therein|
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