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    Flow directing member for gas turbine engine
    1.
    发明授权
    Flow directing member for gas turbine engine 有权
    燃气轮机发动机导流构件

    公开(公告)号：US08721291B2

    公开(公告)日：2014-05-13

    申请号：US13180578

    申请日：2011-07-12

    Applicant: Ching-Pang Lee ,  Kok-Mun Tham ,  Paul H. Vitt ,  Stephen R. Williamson ,  Matthew D. Montgomery ,  Chander Prakash ,  Melissa Harris

    Inventor： Ching-Pang Lee ,  Kok-Mun Tham ,  Paul H. Vitt ,  Stephen R. Williamson ,  Matthew D. Montgomery ,  Chander Prakash ,  Melissa Harris

    IPC: F01D5/14

    CPC classification number: F01D5/081 ,  F01D5/141 ,  F05D2240/81 ,  F05D2270/17

    Abstract: In a gas turbine engine, a flow directing member includes a platform supported on a rotor and includes a radially facing endwall and at least one axially facing axial surface extending radially inwardly from a junction with the endwall. The flow directing member further includes an airfoil extending radially outwardly from the endwall and a fluid flow directing feature. The fluid flow directing feature includes a groove extending axially into the axial surface. The groove has a radially inner groove end and a radially outer groove end, wherein the outer groove end defines an axially extending notch in the junction between the axial surface and the endwall and forms an opening in the endwall for directing a cooling fluid to the endwall.

    Abstract translation: 在燃气涡轮发动机中，流动引导构件包括支撑在转子上的平台，并且包括径向面向的端壁和至少一个轴向面向轴向表面，该轴向表面从与所述端壁的连接处径向向内延伸。 导流构件还包括从端壁径向向外延伸的翼型件和流体流动引导构件。 流体流动导向特征包括轴向延伸到轴向表面的凹槽。 凹槽具有径向内槽端部和径向外槽端部，其中外槽端部在轴向表面和端壁之间的连接处限定轴向延伸的凹口，并在端壁中形成开口，用于将冷却流体引导到端壁 。

    Plasma actuator controlled film cooling
    2.
    发明授权
    Plasma actuator controlled film cooling 失效
    等离子执行器控制膜冷却

    公开(公告)号：US08500404B2

    公开(公告)日：2013-08-06

    申请号：US12770932

    申请日：2010-04-30

    Applicant: Matthew D. Montgomery ,  Chander Prakash

    Inventor： Matthew D. Montgomery ,  Chander Prakash

    IPC: F01D5/18

    CPC classification number: F01D5/186 ,  F05D2260/202 ,  F05D2270/172

    Abstract: A film cooling apparatus with a cooling hole (46) in a component wall (40). A first surface (42) of the wall is subject to a hot gas flow (48). A second surface (44) receives a coolant gas (50). The coolant flows through the hole, then downstream over the first surface (42). One or more pairs of cooperating electrodes (60-61, 62-63, 80-81) generates and accelerates a plasma (70) that creates a body force acceleration (71, 82) in the coolant flow that urges the coolant flow to turn around the entry edge (57) and/or the exit edge (58) of the cooling hole without separating from the adjacent surface (47, 42). The electrodes may have a geometry that spreads the coolant into a fan shape over the hot surface (42) of the component wall (40).

    Abstract translation: 一种在组件壁（40）中具有冷却孔（46）的薄膜冷却装置。 壁的第一表面（42）经受热气流（48）。 第二表面（44）接收冷却剂气体（50）。 冷却剂流过孔，然后流过第一表面（42）的下游。 一对或多对配合电极（60-61,62-63,80-81）产生并加速等离子体（70），其产生在促使冷却剂流转向的冷却剂流中的体力加速度（71,82） 围绕冷却孔的入口边缘（57）和/或出口边缘（58），而不与相邻表面（47,42）分离。 电极可以具有将冷却剂扩散到组件壁（40）的热表面（42）上的扇形形状的几何形状。

    Plasma induced flow control of boundary layer at airfoil endwall
    3.
    发明授权
    Plasma induced flow control of boundary layer at airfoil endwall 失效
    翼型端壁边界层等离子体诱导流量控制

    公开(公告)号：US08435001B2

    公开(公告)日：2013-05-07

    申请号：US12640242

    申请日：2009-12-17

    Applicant: Matthew D. Montgomery ,  Ching-Pang Lee ,  Chander Prakash

    Inventor： Matthew D. Montgomery ,  Ching-Pang Lee ,  Chander Prakash

    IPC: F01D9/00

    CPC classification number: F01D5/145 ,  F05D2270/172 ,  Y02T50/67 ,  Y02T50/673

    Abstract: Plasma generators (48, 49, 70, 71) in an endwall (25) of an airfoil (22) induce aerodynamic flows in directions (50) that modify streamlines (47) of the endwall boundary layer toward a streamline geometry (46) of a midspan region of the airfoil. This reduces vortices (42) generated by the momentum deficit of the boundary layer, increasing aerodynamic efficiency. The plasma generators may be arrayed around the leading edge as well as between two airfoils (22) in a gas turbine nozzle structure, and may be positioned at correction points (68) in streamlines caused by surface contouring (66) of the endwall. The plasma generators may be oriented to generate flow vectors (74) that combine with boundary layer flow vectors (72) to produce resultant flow vectors (76) in directions that reduce turbulence.

    Abstract translation: 翼型件（22）的端壁（25）中的等离子体发生器（48,49,70,71）在方向（50）上引起空气动力学流动，所述方向（50）将端壁边界层的流线（47）改变为流线几何形状（46） 翼型的跨跨区域。 这减少了由边界层的动量缺失产生的旋涡（42），从而提高了空气动力学效率。 等离子体发生器可以围绕前缘以及在燃气涡轮喷嘴结构中的两个翼型件（22）之间排列，并且可以位于由端壁的表面轮廓（66）引起的流线中的校正点（68）处。 等离子体发生器可以被定向以产生与边界层流向量（72）组合的流向量（74），以在减少湍流的方向上产生合成流向量（76）。

    PLASMA ACTUATOR CONTROLLED FILM COOLING
    4.
    发明申请
    PLASMA ACTUATOR CONTROLLED FILM COOLING 失效
    等离子体执行器控制膜冷却

    公开(公告)号：US20110268556A1

    公开(公告)日：2011-11-03

    申请号：US12770932

    申请日：2010-04-30

    Applicant: Matthew D. Montgomery ,  Chander Prakash

    Inventor： Matthew D. Montgomery ,  Chander Prakash

    IPC: F04D29/58

    CPC classification number: F01D5/186 ,  F05D2260/202 ,  F05D2270/172

    Abstract: A film cooling apparatus with a cooling hole (46) in a component wall (40). A first surface (42) of the wall is subject to a hot gas flow (48). A second surface (44) receives a coolant gas (50). The coolant flows through the hole, then downstream over the first surface (42). One or more pairs of cooperating electrodes (60-61, 62-63, 80-81) generates and accelerates a plasma (70) that creates a body force acceleration (71, 82) in the coolant flow that urges the coolant flow to turn around the entry edge (57) and/or the exit edge (58) of the cooling hole without separating from the adjacent surface (47, 42). The electrodes may have a geometry that spreads the coolant into a fan shape over the hot surface (42) of the component wall (40).

    Abstract translation: 一种在组件壁（40）中具有冷却孔（46）的薄膜冷却装置。 壁的第一表面（42）经受热气流（48）。 第二表面（44）接收冷却剂气体（50）。 冷却剂流过孔，然后流过第一表面（42）的下游。 一对或多对配合电极（60-61,62-63,80-81）产生并加速等离子体（70），其产生在促使冷却剂流转向的冷却剂流中的体力加速度（71,82） 围绕冷却孔的入口边缘（57）和/或出口边缘（58），而不与相邻表面（47,42）分离。 电极可以具有将冷却剂扩散到组件壁（40）的热表面（42）上的扇形形状的几何形状。

    Plasma Induced Flow Control of Boundary Layer at Airfoil Endwall
    5.
    发明申请
    Plasma Induced Flow Control of Boundary Layer at Airfoil Endwall 失效
    翼型端壁边界层等离子体诱导流量控制

    公开(公告)号：US20110150653A1

    公开(公告)日：2011-06-23

    申请号：US12640242

    申请日：2009-12-17

    Applicant: Matthew D. Montgomery ,  Ching-Pang Lee ,  Chander Prakash

    Inventor： Matthew D. Montgomery ,  Ching-Pang Lee ,  Chander Prakash

    IPC: F01D5/14 ,  F01D9/02

    CPC classification number: F01D5/145 ,  F05D2270/172 ,  Y02T50/67 ,  Y02T50/673

    Abstract: Plasma generators (48, 49, 70, 71) in an endwall (25) of an airfoil (22) induce aerodynamic flows in directions (50) that modify streamlines (47) of the endwall boundary layer toward a streamline geometry (46) of a midspan region of the airfoil. This reduces vortices (42) generated by the momentum deficit of the boundary layer, increasing aerodynamic efficiency. The plasma generators may be arrayed around the leading edge as well as between two airfoils (22) in a gas turbine nozzle structure, and may be positioned at correction points (68) in streamlines caused by surface contouring (66) of the endwall. The plasma generators may be oriented to generate flow vectors (74) that combine with boundary layer flow vectors (72) to produce resultant flow vectors (76) in directions that reduce turbulence.

    Abstract translation: 翼型件（22）的端壁（25）中的等离子体发生器（48,49,70,71）在方向（50）上引起空气动力学流动，所述方向（50）将端壁边界层的流线（47）改变为流线几何形状（46） 翼型的跨跨区域。 这减少了由边界层的动量缺失产生的旋涡（42），从而提高了空气动力学效率。 等离子体发生器可以围绕前缘以及在燃气涡轮喷嘴结构中的两个翼型件（22）之间排列，并且可以位于由端壁的表面轮廓（66）引起的流线中的校正点（68）处。 等离子体发生器可以被定向以产生与边界层流向量（72）组合的流向量（74），以在减少湍流的方向上产生合成流向量（76）。

    FLOW DIRECTING MEMBER FOR GAS TURBINE ENGINE
    6.
    发明申请
    FLOW DIRECTING MEMBER FOR GAS TURBINE ENGINE 有权
    用于气体涡轮发动机的流动导向构件

    公开(公告)号：US20130017095A1

    公开(公告)日：2013-01-17

    申请号：US13180578

    申请日：2011-07-12

    Applicant: Ching-Pang Lee ,  Kok-Mun Tham ,  Paul H. Vitt ,  Stephen R. Williamson ,  Matthew D. Montgomery ,  Chander Prakash ,  Melissa Harris

    Inventor： Ching-Pang Lee ,  Kok-Mun Tham ,  Paul H. Vitt ,  Stephen R. Williamson ,  Matthew D. Montgomery ,  Chander Prakash ,  Melissa Harris

    IPC: F01D5/14

    CPC classification number: F01D5/081 ,  F01D5/141 ,  F05D2240/81 ,  F05D2270/17

    Abstract: In a gas turbine engine, a flow directing member includes a platform supported on a rotor and includes a radially facing endwall and at least one axially facing axial surface extending radially inwardly from a junction with the endwall. The flow directing member further includes an airfoil extending radially outwardly from the endwall and a fluid flow directing feature. The fluid flow directing feature includes a groove extending axially into the axial surface. The groove has a radially inner groove end and a radially outer groove end, wherein the outer groove end defines an axially extending notch in the junction between the axial surface and the endwall and forms an opening in the endwall for directing a cooling fluid to the endwall.

    Abstract translation: 在燃气涡轮发动机中，流动引导构件包括支撑在转子上的平台，并且包括径向面向的端壁和至少一个轴向面向轴向表面，该轴向表面从与所述端壁的连接处径向向内延伸。 导流构件还包括从端壁径向向外延伸的翼型件和流体流动引导构件。 流体流动导向特征包括轴向延伸到轴向表面的凹槽。 凹槽具有径向内槽端部和径向外槽端部，其中外槽端部在轴向表面和端壁之间的连接处限定轴向延伸的凹口，并在端壁中形成开口，用于将冷却流体引导到端壁 。

    SEAL INCLUDING FLEXIBLE SEAL STRIPS
    8.
    发明申请
    SEAL INCLUDING FLEXIBLE SEAL STRIPS 有权
    密封包括柔性密封条

    公开(公告)号：US20120007318A1

    公开(公告)日：2012-01-12

    申请号：US12832141

    申请日：2010-07-08

    Applicant: Ching-Pang Lee ,  Vincent P. Laurello ,  Chander Prakash ,  Kok-Mun Tham

    Inventor： Ching-Pang Lee ,  Vincent P. Laurello ,  Chander Prakash ,  Kok-Mun Tham

    IPC: F02F11/00 ,  F16J15/44

    CPC classification number: F16J15/3292 ,  F01D11/02 ,  F05D2240/57

    Abstract: A seal member for effecting a seal preventing fluid flow in an axial direction through an annular space formed between two relatively moving components including a rotatable shaft and a stator structure. The seal member includes a plurality of flexible seal strips. Each seal strip includes a planar plate extending radially through the annular space and having a radially outer end supported to the stator structure and a radially inner end defining a tip portion extending widthwise in the axial direction engaged in sliding contact with a peripheral surface of the rotatable shaft. At least one of the seal strips includes a plurality of perforations extending through the seal strip and located between a leading edge and a trailing edge of the seal strip for effecting an increased flexibility of the seal strip adjacent to the tip portion.

    Abstract translation: 一种用于实现密封的密封件，其防止流体沿轴向流动通过形成在包括可旋转轴和定子结构的两个相对移动部件之间的环形空间。 密封构件包括多个柔性密封条。 每个密封条包括平面板，该平面板径向地延伸穿过环形空间并且具有支撑到定子结构的径向外端，以及限定沿轴向方向沿宽度方向延伸的尖端部分的径向内端，该尖端部分与可旋转的 轴。 密封条中的至少一个包括延伸穿过密封条并且位于密封条的前缘和后缘之间的多个穿孔，用于实现与尖端部分相邻的密封条的增加的柔性。

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