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    Turbine airfoil with curved squealer tip
    1.
    发明授权
    Turbine airfoil with curved squealer tip 有权
    涡轮翼型具有弯曲的尖叫

    公开(公告)号：US07290986B2

    公开(公告)日：2007-11-06

    申请号：US11162433

    申请日：2005-09-09

    申请人： Mark Edward Stegemiller ,  Chander Prakash ,  Leslie Eugene Leeke ,  Kevin Samuel Klasing ,  Ching-Pang Lee

    发明人： Mark Edward Stegemiller ,  Chander Prakash ,  Leslie Eugene Leeke ,  Kevin Samuel Klasing ,  Ching-Pang Lee

    IPC分类号： F01D5/20

    CPC分类号： F01D5/20 ,  F05D2250/71 ,  F05D2250/712 ,  Y02T50/67

    摘要： An airfoil for a gas turbine engine includes a root, a tip, a leading edge, a trailing edge, and opposed pressure and suction sidewalls extending generally along a radial axis. The airfoil includes a tip cap extending between the pressure and suction sidewalls; and spaced-apart suction-side and pressure-side tip walls extending radially outward from the tip cap to define a tip cavity therebetween. The pressure-side tip wall includes a continuously concave curved arcuate portion, at least a section of which extends circumferentially outward from a radial axis of the airfoil.

    摘要翻译： 用于燃气涡轮发动机的翼型件包括根部，尖端，前缘，后缘以及大致沿径向轴线延伸的相对的压力和吸力侧壁。 翼型件包括在压力侧和吸力侧壁之间延伸的顶盖; 并且间隔开的吸入侧和压力侧尖端壁从尖端帽径向向外延伸以在它们之间限定尖端腔。 压力侧末端壁包括连续凹入的弯曲弧形部分，其至少一部分从翼型件的径向轴向向外延伸。

    Turbine blade frequency tuned pin bank
    2.
    发明授权
    Turbine blade frequency tuned pin bank 有权
    涡轮叶片频率调谐针库

    公开(公告)号：US07008179B2

    公开(公告)日：2006-03-07

    申请号：US10737428

    申请日：2003-12-16

    申请人： Gerard Anthony Rinck ,  Jonathan Philip Clarke ,  Mark Edward Stegemiller ,  Hardev Singh ,  Steven Robert Brassfield

    发明人： Gerard Anthony Rinck ,  Jonathan Philip Clarke ,  Mark Edward Stegemiller ,  Hardev Singh ,  Steven Robert Brassfield

    IPC分类号： F01D25/36

    CPC分类号： F01D5/16 ,  F05D2260/96 ,  Y10S416/50

    摘要： A gas turbine engine turbine blade includes a hollow airfoil extending radially from a blade root to a radially outer airfoil tip. The airfoil includes an airfoil outer wall having transversely spaced apart pressure and suction side walls meeting along chordally spaced apart leading and trailing edges of the airfoil. A radially extending cooling air supply channel within the airfoil includes a bank of pins integral with and extending transversely between the pressure and suction side walls. The bank of the pins is tuned such that a natural frequency of the blade associated with an engine forced driving mode of the blade is sufficiently away from a steady state engine operating frequency to substantially avoid natural frequency resonance of the blade during steady state engine operation. The bank of the pins is tuned by locations of the pins within the cooling air supply channel.

    摘要翻译： 燃气涡轮发动机涡轮机叶片包括从叶片根部径向延伸到径向外部翼型端头的中空翼型件。 翼型件包括翼型件外壁，其具有横向间隔开的压力和抽吸侧壁，其沿翼型间隔开的前缘和后缘相交。 翼型件内的径向延伸的冷却空气供应通道包括与压力侧和侧壁之间横向间隔并横向延伸的一排销。 调整销的组，使得与发动机的发动机强制驱动模式相关联的叶片的固有频率足够远离稳态发动机工作频率，以便在稳态发动机操作期间基本上避免叶片的固有频率共振。 引脚的组合由冷却空气供应通道中的销的位置调节。

    Fourth-stage turbine bucket airfoil
    7.
    发明授权
    Fourth-stage turbine bucket airfoil 失效
    第四级涡轮机桶翼型

    公开(公告)号：US06503059B1

    公开(公告)日：2003-01-07

    申请号：US09899543

    申请日：2001-07-06

    申请人： Wilson Frost ,  Mark Edward Stegemiller ,  Andrew Charles Powis ,  Peter P. Pirolla ,  David John Humanchuk ,  Gunnar Leif Siden

    发明人： Wilson Frost ,  Mark Edward Stegemiller ,  Andrew Charles Powis ,  Peter P. Pirolla ,  David John Humanchuk ,  Gunnar Leif Siden

    IPC分类号： F01D514

    CPC分类号： F01D5/141 ,  F05D2240/301 ,  Y10S416/02

    摘要： The fourth-stage buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I wherein Z is a perpendicular distance from a plane normal to a radius of the turbine centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at the radially innermost aerodynamic section of the airfoil and X and Y are coordinate values defining the airfoil profile at each distance Z. The X, Y and Z values may be scaled as a function of the same constant or number to provide a scaled-up or scaled-down airfoil section for the bucket.

    摘要翻译： 第四级铲斗具有基本上符合表I中以英寸表示的X，Y和Z的笛卡尔坐标值的翼型，其中Z是垂直于涡轮机中心线半径的平面的垂直距离，并且包含X和 Y值在Z轴的X，Y平面上从零开始，X和Y在翼型的径向最内空气动力学部分处开始，X和Y是定义每个距离Z处的翼面轮廓的坐标值.X，Y和Z值可以被缩放 作为相同常数或数字的函数，以提供用于铲斗的放大或缩小的翼型部分。