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    Turbine blade with serpentine channels
    1.
    发明授权
    Turbine blade with serpentine channels 有权

    公开(公告)号：US10895168B2

    公开(公告)日：2021-01-19

    申请号：US16427144

    申请日：2019-05-30

    Applicant: Solar Turbines Incorporated

    Inventor： Hongzhou Xu

    IPC: F01D5/18 ,  F01D25/12

    Abstract: A turbine blade having a base and an airfoil, the base including a root end. The airfoil including a skin extending from the base and defining a leading edge, a trailing edge, having a tip end opposite from the root end. The turbine blade further including dividers located within the airfoil. The dividers, leading edge, trailing edge, and skin define serpentine channels within the airfoil. A first multi-bend heat exchange path and a second multi-bend heat exchange path extend through the serpentine channels to cool portion of the turbine blade.

    GAS TURBINE ENGINE TURBINE DIAPHRAGM WITH ANGLED HOLES
    3.
    发明申请
    GAS TURBINE ENGINE TURBINE DIAPHRAGM WITH ANGLED HOLES 有权
    燃气涡轮发动机涡轮叶片带有光滑的孔

    公开(公告)号：US20140086727A1

    公开(公告)日：2014-03-27

    申请号：US13627946

    申请日：2012-09-26

    Applicant: SOLAR TURBINES INCORPORATED

    Inventor： Hongzhou Xu

    IPC: F01D25/12 ,  B23P17/00

    CPC classification number: F01D5/082 ,  F01D5/085 ,  F01D9/04 ,  F01D11/001 ,  F01D11/04 ,  F05D2240/128 ,  F05D2250/191 ,  F05D2260/14 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/941 ,  Y10T29/49229

    Abstract: A gas turbine engine turbine diaphragm (460) includes an inner cylindrical portion (461), a mounting portion (463), and a disk portion (462). The mounting portion (463) is located radially outward from the inner cylindrical portion (461). The disk portion (462) extends radially between the inner cylindrical portion (461) and the mounting portion (463). The disk portion (462) includes a plurality of angled holes (464). Each angled hole (464) follows a vector which is angled in at least one plane. A component of the vector is located on a plane perpendicular to a radial extending from an axis of the diaphragm (460). The component of the vector is angled relative to an axial direction of the diaphragm (460).

    Abstract translation: 燃气涡轮发动机涡轮隔膜（460）包括内圆柱部分（461），安装部分（463）和圆盘部分（462）。 安装部分（463）从内圆柱形部分（461）径向向外定位。 圆盘部分（462）在内圆柱形部分（461）和安装部分（463）之间径向延伸。 盘部分（462）包括多个成角度的孔（464）。 每个倾斜孔（464）遵循在至少一个平面中成角度的矢量。 矢量的分量位于垂直于从膜片（460）的轴线延伸的径向的平面上。 矢量的分量相对于隔膜（460）的轴向方向成角度。

    TURBINE BLADE WITH SERPENTINE CHANNELS
    5.
    发明申请
    TURBINE BLADE WITH SERPENTINE CHANNELS 审中-公开

    公开(公告)号：US20200378263A1

    公开(公告)日：2020-12-03

    申请号：US16427144

    申请日：2019-05-30

    Applicant: Solar Turbines Incorporated

    Inventor： Hongzhou Xu

    IPC: F01D5/18 ,  F01D5/20 ,  F01D25/12

    Abstract: A turbine blade having a base and an airfoil, the base including a root end. The airfoil including a skin extending from the base and defining a leading edge, a trailing edge, having a tip end opposite from the root end. The turbine blade further including dividers located within the airfoil. The dividers, leading edge, trailing edge, and skin define serpentine channels within the airfoil. A first multi-bend heat exchange path and a second multi-bend heat exchange path extend through the serpentine channels to cool portion of the turbine blade.

    Turbine blade with a coupled serpentine channel
    6.
    发明授权
    Turbine blade with a coupled serpentine channel 有权

    公开(公告)号：US10731478B2

    公开(公告)日：2020-08-04

    申请号：US16217953

    申请日：2018-12-12

    Applicant: Solar Turbines Incorporated

    Inventor： Hongzhou Xu ,  Kevin Liu ,  Michael D. Fox

    IPC: F01D5/18 ,  F01D5/30 ,  F01D5/14

    Abstract: A turbine blade having a base and an airfoil, the base including a root end. The airfoil including a skin extending from the base and defining a first edge, a second edge, having a tip end opposite from the root end. The turbine blade further including a base rib extending from the base and into the airfoil, a center divider extending from adjacent the first edge towards the second edge, a center rib disposed between the center divider and the second edge, extending from adjacent the center divider towards the tip end and extending from adjacent the center divider towards the root end, a tip center rib extending from adjacent the second edge towards the first edge, a tip rib extending from adjacent the tip center rib towards the base, a dividing rib and a first channel.

    Gas turbine engine turbine diaphragm with angled holes
    7.
    发明授权
    Gas turbine engine turbine diaphragm with angled holes 有权
    带有斜孔的燃气涡轮发动机涡轮隔膜

    公开(公告)号：US09169729B2

    公开(公告)日：2015-10-27

    申请号：US13627946

    申请日：2012-09-26

    Applicant: Solar Turbines Incorporated

    Inventor： Hongzhou Xu

    IPC: F01D9/04 ,  F01D5/08 ,  F01D11/00 ,  F01D11/04

    CPC classification number: F01D5/082 ,  F01D5/085 ,  F01D9/04 ,  F01D11/001 ,  F01D11/04 ,  F05D2240/128 ,  F05D2250/191 ,  F05D2260/14 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/941 ,  Y10T29/49229

    Abstract: A gas turbine engine turbine diaphragm (460) includes an inner cylindrical portion (461), a mounting portion (463), and a disk portion (462). The mounting portion (463) is located radially outward from the inner cylindrical portion (461). The disk portion (462) extends radially between the inner cylindrical portion (461) and the mounting portion (463). The disk portion (462) includes a plurality of angled holes (464). Each angled hole (464) follows a vector which is angled in at least one plane. A component of the vector is located on a plane perpendicular to a radial extending from an axis of the diaphragm (460). The component of the vector is angled relative to an axial direction of the diaphragm (460).

    Abstract translation: 燃气涡轮发动机涡轮隔膜（460）包括内圆柱部分（461），安装部分（463）和圆盘部分（462）。 安装部分（463）从内圆柱形部分（461）径向向外定位。 圆盘部分（462）在内圆柱形部分（461）和安装部分（463）之间径向延伸。 盘部分（462）包括多个成角度的孔（464）。 每个倾斜孔（464）遵循在至少一个平面中成角度的矢量。 矢量的分量位于垂直于从膜片（460）的轴线延伸的径向的平面上。 矢量的分量相对于隔膜（460）的轴向方向成角度。

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