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    Turbine airfoil profile
    2.
    发明授权
    Turbine airfoil profile 有权

    公开(公告)号：US11454120B2

    公开(公告)日：2022-09-27

    申请号：US16212950

    申请日：2018-12-07

    申请人： General Electric Company

    发明人： Adam Fredmonski ,  Moorthi Subramaniyan

    IPC分类号： F01D5/14 ,  F04D29/38 ,  F04D29/66

    摘要： A turbine blade for a rotary machine includes an airfoil that extends from a root to a tip along a radial span. The airfoil further includes a first sidewall and a second sidewall that are coupled together at a leading edge of the airfoil and that extend aftward to a trailing edge of the airfoil. One of the first sidewall or the second sidewall includes a tip region having an increased stagger angle that produces a non-linear, over-hanging trailing edge.

    AIRFOIL SHAPE FOR THIRTEENTH STAGE COMPRESSOR STATOR VANE
    3.
    发明申请
    AIRFOIL SHAPE FOR THIRTEENTH STAGE COMPRESSOR STATOR VANE 审中-公开

    公开(公告)号：US20180087530A1

    公开(公告)日：2018-03-29

    申请号：US15279004

    申请日：2016-09-28

    申请人： General Electric Company

    发明人： Moorthi Subramaniyan ,  Sagar Kamble

    IPC分类号： F04D29/54 ,  F04D29/32 ,  F04D29/38 ,  F02C3/04

    CPC分类号： F04D29/544 ,  F01D5/141 ,  F04D29/324 ,  F05D2250/74 ,  Y02T50/673

    摘要： A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.

    AIRFOIL TRAILING EDGE
    4.
    发明申请
    AIRFOIL TRAILING EDGE 审中-公开

    公开(公告)号：US20150063997A1

    公开(公告)日：2015-03-05

    申请号：US14013661

    申请日：2013-08-29

    申请人： GENERAL ELECTRIC COMPANY

    发明人： Sunil Rajagopal ,  Moorthi Subramaniyan ,  Lakshmanan Valliappan

    IPC分类号： F01D5/14 ,  F01D9/02

    CPC分类号： F01D5/141 ,  F01D5/145 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2250/184 ,  Y02T50/673

    摘要： An airfoil includes a radially inner edge extending in a radial direction of the airfoil to a radially outer edge. Also included is a leading edge extending in an axial direction of the airfoil to a trailing edge. Further included is a trailing edge geometry comprising at least one wave segment having simultaneous curvature in at least two directions.

    摘要翻译： 翼型件包括沿翼型件的径向方向延伸到径向外边缘的径向内边缘。 还包括沿翼型的轴向方向延伸到后缘的前缘。 还包括后缘几何形状，其包括至少一个在至少两个方向具有同时曲率的波段。

    Exhaust diffuser
    7.
    发明授权
    Exhaust diffuser 有权
    排气扩散器

    公开(公告)号：US09359900B2

    公开(公告)日：2016-06-07

    申请号：US13646003

    申请日：2012-10-05

    申请人： General Electric Company

    发明人： Manjunath Bangalore Chengappa ,  Moorthi Subramaniyan ,  Vignesh Radhakrishnan

    IPC分类号： F02C7/00 ,  F01N13/00 ,  F02C3/04 ,  F01D5/14 ,  F01D25/30

    CPC分类号： F01D5/145 ,  F01D25/30 ,  F05D2240/127

    摘要： An exhaust diffuser includes an outer shroud and an inner shroud radially separated from the outer shroud so as to define a fluid passage between the outer shroud and the inner shroud. A strut extends between the outer shroud and the inner shroud. The strut generally includes an outer surface, a leading edge, a trailing edge, a first side and a second side. At least one turbulator may be positioned along a radial span of the strut. The at least one turbulator extends generally outwardly from the strut outer surface. The turbulator extends across the leading edge of the strut from the first side to the second side of the strut.

    摘要翻译： 排气扩散器包括外护罩和与外护罩径向分离的内护罩，以便在外护罩和内护罩之间限定流体通道。 支柱在外护罩和内护罩之间延伸。 支柱通常包括外表面，前缘，后缘，第一侧和第二侧。 至少一个湍流器可以沿着支柱的径向跨度定位。 至少一个湍流器从支柱外表面大致向外延伸。 湍流器从支柱的前缘延伸穿过支柱的第一侧到第二侧。

    EXHAUST GAS DIFFUSER FOR A GAS TURBINE
    9.
    发明申请
    EXHAUST GAS DIFFUSER FOR A GAS TURBINE 审中-公开
    用于气体涡轮的排气歧管

    公开(公告)号：US20140137533A1

    公开(公告)日：2014-05-22

    申请号：US13680420

    申请日：2012-11-19

    申请人： GENERAL ELECTRIC COMPANY

    发明人： Moorthi Subramaniyan ,  Manjunath Bangalore Chengappa

    IPC分类号： F01D25/30

    CPC分类号： F01D25/30 ,  F05D2250/292

    摘要： An exhaust gas diffuser for a gas turbine generally includes an inner wall that extends along an axial centerline of the exhaust gas diffuser. An outer wall is coaxially aligned with the inner wall. The outer wall is radially separated from the inner wall so as to define a flow passage therebetween. An airfoil shaped strut is disposed in the flow passage. The strut extends between the inner and the outer walls. The strut includes a leading edge and a trailing edge positioned relative to a direction of flow through the flow passage. The leading edge and the trailing edge are tapered from the inner wall to the outer wall in the direction of flow through the passage.

    摘要翻译： 用于燃气轮机的排气扩散器通常包括沿着排气扩散器的轴向中心线延伸的内壁。 外壁与内壁同轴对准。 外壁与内壁径向分开，以便在它们之间限定一个流动通道。 翼型支柱设置在流动通道中。 支柱在内壁和外壁之间延伸。 支柱包括相对于流过流动通道的流动方向定位的前缘和后缘。 前缘和后缘在流过通道的方向上从内壁到外壁逐渐变细。

    TURBINE BLADE WITH NON-AXISYMMETRIC FORWARD FEATURE
    10.
    发明申请
    TURBINE BLADE WITH NON-AXISYMMETRIC FORWARD FEATURE 有权

    公开(公告)号：US20220082023A1

    公开(公告)日：2022-03-17

    申请号：US17025100

    申请日：2020-09-18

    申请人： General Electric Company

    发明人： Moorthi Subramaniyan ,  Adam John Fredmonski

    IPC分类号： F01D5/14 ,  F01D5/18 ,  F01D5/08

    摘要： Turbine blades with non-axisymmetric forward features are provided. A turbine blade may include a platform and an airfoil extending radially outward from the platform and configured to extend into a fluid flowpath. The airfoil separates an upstream portion of the fluid flowpath from a downstream portion of the fluid flowpath. A sealing member extends axially from the platform toward a stationary nozzle adjacent the platform and separates the fluid flowpath from a wheel space. The platform may have a forward face between the sealing member and the airfoil and, optionally, a forward axial face between the forward face and the airfoil. The forward face or forward axial face may face the upstream portion of the fluid flowpath and may have a profile that is non-axisymmetric with respect to its centerline axis.