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    LAST STAGE AIRFOIL DESIGN FOR OPTIMAL DIFFUSER PERFORMANCE
    23.
    发明申请
    LAST STAGE AIRFOIL DESIGN FOR OPTIMAL DIFFUSER PERFORMANCE 审中-公开

    公开(公告)号：US20170130587A1

    公开(公告)日：2017-05-11

    申请号：US14936253

    申请日：2015-11-09

    Applicant: General Electric Company

    Inventor： Soumyik Kumar Bhaumik ,  Brian Denver Potter ,  Rohit Chouhan ,  Georgia Fleming Brunt

    IPC: F01D5/14 ,  F02C3/04

    CPC classification number: F01D5/145 ,  F01D5/141 ,  F01D5/147 ,  F01D9/041 ,  F02C3/04 ,  F05D2220/32 ,  F05D2220/3215 ,  F05D2240/301 ,  F05D2240/35 ,  F05D2250/70

    Abstract: A system includes a turbine airfoil configured to be disposed in a turbine. The airfoil includes a suction side, a pressure side, and a first protrusion disposed on the suction side, a second protrusion disposed on the pressure side, or both. The suction side extends between a leading edge of the turbine airfoil and a trailing edge of the turbine airfoil in an axial direction and transverse to a longitudinal axis of the turbine airfoil, and extends a height of the turbine airfoil in a radial direction along the longitudinal axis. The pressure side is disposed opposite the suction side and extends between the leading edge of the turbine airfoil and the trailing edge of the turbine airfoil in the axial direction, and extends the height of the airfoil in the radial direction. The first protrusion is disposed on the suction side of the turbine airfoil and protrudes relative to the other portion of the suction side in a first direction transverse to both the radial and axial directions. The second protrusion is disposed on the pressure side of the turbine airfoil and protrudes relative to the other portion of the pressure side in a second direction transverse to both the radial and axial directions, and opposite the first direction.

    Airfoil for gas turbine, blade and vane
    28.
    发明授权
    Airfoil for gas turbine, blade and vane 有权
    用于燃气轮机，叶片和叶片的翼型

    公开(公告)号：US09581027B2

    公开(公告)日：2017-02-28

    申请号：US14280927

    申请日：2014-05-19

    Applicant: ALSTOM Technology Ltd

    Inventor： Marcin Romanowski ,  Marcel Koenig ,  Laura Bogdanic

    IPC: F01D5/14

    CPC classification number: F01D5/14 ,  F01D5/143 ,  F01D5/145

    Abstract: The invention relates to an airfoil for a gas turbine, which comprises a compound fillet disposed between the airfoil and a platform. The compound fillet consists of a first arc and a second arc. A first end of the first arc tangentially adjoins an outer surface of the airfoil. A second end of the first arc tangentially adjoins a first end of the second arc. A second end of the second arc tangentially adjoins a surface of the platform, wherein the following equation is satisfied: 0.15≦R1/s≦0.45, and 0.09≦a/s≦0.27.

    Abstract translation: 本发明涉及一种用于燃气轮机的翼型件，其包括设置在翼型件和平台之间的复合圆角。 复合圆角由第一弧和第二弧组成。 第一弧的第一端切向地邻接翼型件的外表面。 第一弧的第二端切向地邻接第二弧的第一端。 第二弧的第二端切向地邻接平台的表面，其中满足以下等式：0.15≤R1/s≤0.45，并且0.09≤a/s≤0.27。

    COMPRESSOR ENDWALL BOUNDARY LAYER REMOVAL
    29.
    发明申请
    COMPRESSOR ENDWALL BOUNDARY LAYER REMOVAL 审中-公开
    压缩机端部边界层拆除

    公开(公告)号：US20170009663A1

    公开(公告)日：2017-01-12

    申请号：US14793572

    申请日：2015-07-07

    Applicant: United Technologies Corporation

    Inventor： Alan H. Epstein

    IPC: F02C9/18

    CPC classification number: F02C9/18 ,  F01D5/145 ,  F04D29/542 ,  F04D29/545 ,  F04D29/682 ,  F05D2220/3216

    Abstract: A compressor is provided. The compressor may comprise a blade configured to rotate about an axis, an inner endwall coupled to the blade, and an outer endwall radially outward from the blade and the inner endwall. The outer endwall and the inner endwall may define a flow path. A vane may be disposed aft of the blade and coupled to the outer endwall, and a bleed passage may be selectively positioned to extract a boundary layer flow. A method of locating bleed passages is also provided. The method may include comprise analyzing at least one an entropy or a temperature of a boundary layer flow, identifying endwall locations where the entropy or the temperature are elevated, and forming a bleed passage at the endwall locations.

    Abstract translation: 提供压缩机。 压缩机可以包括构造成围绕轴线旋转的叶片，联接到叶片的内端壁和从叶片和内端壁径向向外的外端壁。 外端壁和内端壁可以限定流路。 叶片可以设置在叶片的后部并且联接到外端壁，并且可以选择性地定位排出通道以提取边界层流。 还提供了一种定位排放通道的方法。 该方法可以包括分析边界层流的至少一个熵或温度，识别熵或温度升高的端壁位置，以及在端壁位置处形成渗流通道。

    Axial Turbine
    30.
    发明申请
    Axial Turbine 审中-公开
    轴流式涡轮机

    公开(公告)号：US20160369654A1

    公开(公告)日：2016-12-22

    申请号：US15182707

    申请日：2016-06-15

    Applicant: Mitsubishi Hitachi Power Systems, Ltd.

    Inventor： Hisataka FUKUSHIMA ,  Takeshi KUDO ,  Shigeki SENOO ,  Hideki ONO

    IPC: F01D25/24 ,  F01D9/04 ,  F01D5/12

    CPC classification number: F01D25/24 ,  F01D5/12 ,  F01D5/145 ,  F01D5/225 ,  F01D9/041 ,  F05D2220/30 ,  F05D2220/31

    Abstract: An axial turbine includes an upstream turbine stage that includes: a cover disposed at a distal end of an upstream bucket and opposed to an inner wall of an upstream diaphragm outer ring across a gap; and a downstream diaphragm outer ring that is disposed downstream of the upstream turbine stage and that has an inner peripheral-side end wall shaped into a flare. The inner peripheral-side end wall of the downstream diaphragm outer ring has a flare angle formed to be greater than a slant angle of an inner peripheral-side wall of the cover. In the axial turbine, the inner peripheral-side end wall of the downstream diaphragm outer ring is formed to have a meridional shape that has at least one inflection point between the upstream turbine stage and a downstream turbine stage and such that a tangent at the inflection point with respect to a steam flow direction has a positive gradient.

    Abstract translation: 轴流式涡轮机包括上游涡轮级，其包括：盖，其设置在上游桶的远端并且跨越间隙与上游隔膜外环的内壁相对; 以及下游隔膜外圈，其设置在上游涡轮机台的下游，并具有成形为火炬的内周侧端壁。 下游隔膜外圈的内周侧端壁具有形成为大于盖的内周侧壁的倾斜角的张开角。 在轴向涡轮机中，下游隔膜外圈的内周侧端壁形成为具有在上游涡轮级与下游涡轮级之间具有至少一个拐点的子午形状，使得在拐点处的切线 相对于蒸汽流动方向的点具有正梯度。

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