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    Turbine blade frequency tuned pin bank
    5.
    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。

    Cluster bridged casting core
    7.
    发明授权
    Cluster bridged casting core 有权
    集群桥接铸铁芯

    公开(公告)号：US07674093B2

    公开(公告)日：2010-03-09

    申请号：US11641286

    申请日：2006-12-19

    申请人： Ching-Pang Lee ,  Steven Robert Brassfield

    发明人： Ching-Pang Lee ,  Steven Robert Brassfield

    IPC分类号： F01D5/18 ,  B22C9/10

    CPC分类号： B22C9/103 ,  F01D5/187 ,  F05D2230/211 ,  F05D2260/202 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

    摘要： A casting core for a turbine blade includes a plurality of rods extending above a shank. The rods define internal cooling channels in the airfoil of the blade, and the shank defines an inlet channel in the dovetail of the blade. A plurality of stubs are clustered together at a bulb joined to the shank and radiate outwardly to integrally join different ones of the rods for increasing strength of the core.

    摘要翻译： 用于涡轮叶片的铸芯包括在柄上方延伸的多个杆。 杆在叶片的翼型中限定内部冷却通道，并且杆在叶片的燕尾形中限定入口通道。 多个短棒在连接到柄的灯泡上聚集在一起并向外辐射以一体地连接不同的杆，以增加芯的强度。

    Chevron film cooled wall
    8.
    发明授权
    Chevron film cooled wall 有权
    雪佛龙薄膜冷却墙

    公开(公告)号：US07328580B2

    公开(公告)日：2008-02-12

    申请号：US10874900

    申请日：2004-06-23

    申请人： Ching-Pang Lee ,  Steven Robert Brassfield ,  Ronald Scott Bunker

    发明人： Ching-Pang Lee ,  Steven Robert Brassfield ,  Ronald Scott Bunker

    IPC分类号： F23R3/42

    CPC分类号： B23K26/384

    摘要： A wall in a gas turbine engine includes inner and outer surfaces having a row of compound chevron film cooling holes extending therethrough. The chevron holes diverge both longitudinally and laterally between an inlet at the wall inner surface and a chevron outlet at the wall outer surface.

    摘要翻译： 燃气涡轮发动机中的壁包括内表面和外表面，其具有穿过其延伸的一排复合人字形薄膜冷却孔。 人字形孔在壁内表面的入口和壁外表面的人字形出口之间纵向和横向分开。

    Method and apparatus for reducing turbine blade temperatures
    9.
    发明授权
    Method and apparatus for reducing turbine blade temperatures 失效
    降低涡轮叶片温度的方法和装置

    公开(公告)号：US07217092B2

    公开(公告)日：2007-05-15

    申请号：US10824283

    申请日：2004-04-14

    申请人： Ching-Pang Lee ,  Aspi Rustom Wadia ,  Steven Robert Brassfield

    发明人： Ching-Pang Lee ,  Aspi Rustom Wadia ,  Steven Robert Brassfield

    IPC分类号： F01D5/18

    CPC分类号： F01D5/187 ,  Y02T50/676

    摘要： An airfoil for a gas turbine engine includes a first sidewall and a second sidewall coupled together at a leading edge and a trailing edge, such that a cavity is defined therebetween. A plurality of rib walls extend at least partially between the first and second sidewalls, wherein the plurality of rib walls define at least one cooling circuit having at least three cooling chambers. At least one row of openings extend through at least one of the rib walls, wherein a first of the cooling chambers supplies cooling fluid to the cavity, and the remaining cooling chambers are coupled in flow communication with the first cooling chamber via the openings.

    摘要翻译： 用于燃气涡轮发动机的翼型件包括在前缘和后缘处联接在一起的第一侧壁和第二侧壁，使得在其间限定空腔。 多个肋壁至少部分地在第一和第二侧壁之间延伸，其中多个肋壁限定至少一个具有至少三个冷却室的冷却回路。 至少一排开口延伸穿过所述肋壁中的至少一个，其中第一冷却室将冷却流体供应到空腔，并且剩余的冷却室经由所述开口与第一冷却室流体连通地联接。

    Third-stage turbine bucket airfoil
    10.
    发明授权
    Third-stage turbine bucket airfoil 失效
    第三级涡轮机叶翼

    公开(公告)号：US06474948B1

    公开(公告)日：2002-11-05

    申请号：US09886406

    申请日：2001-06-22

    申请人： Peter Paul Pirolla ,  Gunnar Leif Siden ,  David John Humanchuk ,  Steven Robert Brassfield ,  Paul Stuart Wilson

    发明人： Peter Paul Pirolla ,  Gunnar Leif Siden ,  David John Humanchuk ,  Steven Robert Brassfield ,  Paul Stuart Wilson

    IPC分类号： F01D514

    CPC分类号： F01D5/141 ,  F05D2240/301 ,  Y10S416/02 ,  Y10S416/05

    摘要： The third-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 coordinates 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： 第三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平面上在X轴和Y轴的径向最内空气动力学部分处开始为零，X和Y是在每个距离Z处定义翼型轮廓的坐标.X，Y和Z值可以被缩放为 相同的常数或数字的功能来提供用于铲斗的放大或缩小的翼型部分。