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20 条记录 (耗时 0.014 秒)

    MISTUNED COMPRESSOR ROTOR WITH HUB SCOOPS
    2.
    发明申请
    MISTUNED COMPRESSOR ROTOR WITH HUB SCOOPS 审中-公开

    公开(公告)号：US20190085868A1

    公开(公告)日：2019-03-21

    申请号：US15706311

    申请日：2017-09-15

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： Karan ANAND ,  Farid ABRARI ,  Ernest ADIQUE ,  Paul AITCHISON ,  Daniel FUDGE ,  Kari HEIKURINEN ,  Paul STONE ,  Tibor URAC ,  Thomas VEITCH

    IPC分类号： F04D29/66 ,  F04D29/32

    摘要： A compressor rotor for a gas turbine engine includes a hub disposed about an axis of rotation and an outer surface forming a radially inner gaspath boundary, the outer surface defining a nominal hub diameter. A circumferential array of blades extends radially outwardly from the hub. A first inter-blade passage is defined between a first set of adjacent blades and has a first throat area. A second inter-blade passage is defined between a second set of adjacent blades and has a second throat area that is smaller than the first throat area. At least one scoop is disposed in the second inter-blade passage, the scoop defining a cavity extending radially into the outer surface of the hub relative to the nominal hub diameter.

    ROTARY AIRFOIL
    3.
    发明申请
    ROTARY AIRFOIL 审中-公开
    旋转气翼

    公开(公告)号：US20160061042A1

    公开(公告)日：2016-03-03

    申请号：US14469948

    申请日：2014-08-27

    申请人： Pratt & Whitney Canada Corp.

    发明人： Hien DUONG ,  Krishna Prasad BALIKE ,  Thomas VEITCH ,  Raman WARIKOO ,  Keegan LOBO

    IPC分类号： F01D5/14

    CPC分类号： F01D5/141 ,  F01D5/145 ,  F04D29/324 ,  F05D2240/303 ,  F05D2250/71

    摘要： A rotary airfoil in a gas turbine engine is provided. The airfoil includes opposed pressure and suction sides joined together at chordally opposite leading and trailing edges. The pressure and suction sides extend in a span direction from a root to a tip. An axial component of a center of gravity of a cross-section taken chordally toward the tip of the airfoil being upstream relative to an axial component of a center of gravity of a cross-section taken chordally toward the root of the airfoil. A method for forming such blade is also presented.

    摘要翻译： 提供了一种在燃气涡轮发动机中的旋转翼型件。 翼型件包括相对的压力和吸力侧面，它们在弦向相对的前缘和后缘处连接在一起。 压力和吸力侧在从根部到尖端的跨度方向上延伸。 横截面的轴向分量是相对于翼型向翼面的根部截取的横截面的重心的轴向分量在翼面上朝向翼型的末端方向向上延伸的横截面的轴向分量。 还提出了一种用于形成这种刀片的方法。

    MULTI-FILM OIL DAMPER WITH TAPERED DAMPER RINGS
    4.
    发明申请
    MULTI-FILM OIL DAMPER WITH TAPERED DAMPER RINGS 审中-公开

    公开(公告)号：US20200300113A1

    公开(公告)日：2020-09-24

    申请号：US16355986

    申请日：2019-03-18

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： Thomas VEITCH ,  David BEAMISH

    IPC分类号： F01D25/04 ,  F16F15/023 ,  F01D25/16 ,  F16C27/02

    摘要： A multi-film oil damper has a housing defining an annular damper cavity between a radially outward wall and radially extending side walls. The annular damper cavity has an oil inlet configured for connection to a source of pressurized oil. A closure ring defines a radially inward boundary of the annular damper cavity. First and second damper rings are nested together coaxially within the annular damper cavity. At least one of the first damper ring and the second damper ring has an axial end radial thickness less than an intermediate-portion radial thickness.

    METHOD TO SEAL DAMPER CAVITY OF MULTI-FILM OIL DAMPER
    5.
    发明申请
    METHOD TO SEAL DAMPER CAVITY OF MULTI-FILM OIL DAMPER 审中-公开

    公开(公告)号：US20200284298A1

    公开(公告)日：2020-09-10

    申请号：US16291384

    申请日：2019-03-04

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： Thomas VEITCH ,  David BEAMISH ,  Philippe BONNIERE

    IPC分类号： F16C32/06 ,  F01D25/16 ,  F16C33/66 ,  F01D25/18

    摘要： A multi-film oil damper suited for accommodating radial movement of a rotary shaft bearing relative to a bearing housing, the multi-film oil damper comprising: an annular damper cavity defined within the bearing housing between a radially outward wall and radially extending side walls; an inner damper ring; an outer damper ring disposed between the inner damper ring and the radially outward wall of the annular damper cavity; wherein the annular damper cavity has an oil inlet in communication with a source of pressurized oil; and wherein a radial thickness of the inner damper ring exceeds a radial thickness of the outer damper ring.

    COMPRESSOR ROTOR AIRFOIL
    6.
    发明申请
    COMPRESSOR ROTOR AIRFOIL 审中-公开

    公开(公告)号：US20170370374A1

    公开(公告)日：2017-12-28

    申请号：US15674865

    申请日：2017-08-11

    申请人： Pratt & Whitney Canada Corp.

    发明人： Hien DUONG ,  Krishna Prasad BALIKE ,  Thomas VEITCH ,  Keegan LOBO ,  Raman WARIKOO

    IPC分类号： F04D29/38 ,  F04D19/00 ,  F04D29/32 ,  F04D19/02 ,  F01D5/14

    摘要： A compressor rotor airfoil in a gas turbine engine is presented. Opposed pressure and suction sides are joined together at chordally opposite leading and trailing edges. The pressure and suction sides extend in a span direction from a root to a tip. A leading edge dihedral angle is defined at a point on the leading edge between a tangent to the airfoil and a vertical. The leading edge dihedral angle has a span-wise distribution. The distribution has at least one inflection point. A method of reducing a rub angle between a compressor rotor blade and a casing surrounding the blade is also presented.