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    Turbine bucket internal core profile
    1.
    发明授权
    Turbine bucket internal core profile 有权
    涡轮桶内芯型材

    公开(公告)号：US09234428B2

    公开(公告)日：2016-01-12

    申请号：US13613922

    申请日：2012-09-13

    申请人： Randall Richard Good ,  Bradley Taylor Boyer ,  Xiaoyong Fu ,  Aaron Ezekiel Smith ,  Jacob C. Perry, II

    发明人： Randall Richard Good ,  Bradley Taylor Boyer ,  Xiaoyong Fu ,  Aaron Ezekiel Smith ,  Jacob C. Perry, II

    IPC分类号： F01D5/14 ,  F01D5/18

    CPC分类号： F01D5/14 ,  F01D5/187

    摘要： Turbine bucket nominal internal core profiles and core insert external profiles are provided. In one embodiment, a turbine bucket includes an airfoil, platform, shank and dovetail. The bucket has a nominal internal core profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Z values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z values by a height of the bucket in inches, and wherein X and Y are non-dimensional values which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z along the bucket, the profile sections at the Z distances being joined smoothly with one another to form said bucket internal core profile.

    摘要翻译： 提供涡轮桶标称内芯型材和芯插件外部型材。 在一个实施例中，涡轮机桶包括翼型件，平台，柄和燕尾榫。 铲斗具有基本上根据表1所示的X，Y和Z的笛卡尔坐标值的标称内部芯轮廓，其中Z值是从0到1的无量纲值，可以通过将Z值乘以Z 以铲斗的高度为英寸，其中X和Y为无量纲值，当通过平滑连续的圆弧连接时，沿着铲斗在每个距离Z处限定内芯轮廓部分，Z距离处的轮廓部分被连接 彼此平滑地形成所述桶内芯轮廓。

    Turbine bucket airfoil profile
    2.
    发明授权
    Turbine bucket airfoil profile 有权
    涡轮斗翼型材

    公开(公告)号：US08740570B2

    公开(公告)日：2014-06-03

    申请号：US13304734

    申请日：2011-11-28

    申请人： Alexander Stein ,  Bradley Taylor Boyer ,  Xiaoyong Fu ,  Randall Richard Good ,  William Scott Zemitis

    发明人： Alexander Stein ,  Bradley Taylor Boyer ,  Xiaoyong Fu ,  Randall Richard Good ,  William Scott Zemitis

    IPC分类号： F01D5/14

    CPC分类号： F01D5/141 ,  F05D2250/74

    摘要： A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.

    摘要翻译： 提供一种涡轮机桶，其包括具有翼型形状的铲斗翼型，铲斗翼型件具有基本上符合表1所示的X，Y和Z的笛卡尔坐标值的标称轮廓，其中X，Y和Z的笛卡尔坐标值 是通过将X，Y和Z的笛卡尔坐标值乘以翼型的高度（英寸），其中X和Y是以英寸为单位的距离，其中，当 通过平滑连续的弧连接，在每个距离Z处限定翼型轮廓部分，Z距离处的翼型轮廓部分彼此平滑地连接以形成完整的翼型形状。

    COOLING STRUCTURES FOR TURBINE ROTOR BLADE TIPS
    3.
    发明申请
    COOLING STRUCTURES FOR TURBINE ROTOR BLADE TIPS 有权
    涡轮转子叶片的冷却结构

    公开(公告)号：US20140037458A1

    公开(公告)日：2014-02-06

    申请号：US13566202

    申请日：2012-08-03

    申请人： Benjamin Paul Lacy ,  Randall Richard Good ,  Brian Gene Brzek

    发明人： Benjamin Paul Lacy ,  Randall Richard Good ,  Brian Gene Brzek

    IPC分类号： F01D5/18

    CPC分类号： F01D5/20 ,  F01D5/186 ,  F05D2250/182

    摘要： A rotor blade for a turbine of a combustion turbine engine having an airfoil that includes a pressure and a suction sidewall defining an outer periphery and a tip portion defining an outer radial end. The tip portion includes a rail that defines a tip cavity. The airfoil includes an interior cooling passage configured to circulate coolant. The rotor blade further includes: a slotted portion of the rail; and at least one film cooling outlet disposed within at least one of the pressure sidewall and the suction sidewall of the airfoil. The film cooling outlet includes a position that is adjacent to the tip portion and in proximity to the slotted portion of the rail.

    摘要翻译： 一种用于燃气涡轮发动机的涡轮机的转子叶片，其具有包括压力的翼型和限定外周的吸力侧壁和限定外径向端的尖端部分。 尖端部分包括限定尖端腔的轨道。 翼型件包括构造成使冷却剂循环的内部冷却通道。 转子叶片还包括：轨道的开槽部分; 以及设置在翼型件的压力侧壁和吸力侧壁中的至少一个内的至少一个薄膜冷却出口。 薄膜冷却出口包括邻近尖端部分并且靠近导轨的开槽部分的位置。

    Article having durable ceramic coating with localized abradable portion
    9.
    发明授权
    Article having durable ceramic coating with localized abradable portion 有权
    具有耐磨陶瓷涂层，具有局部耐磨部分

    公开(公告)号：US06358002B1

    公开(公告)日：2002-03-19

    申请号：US09371250

    申请日：1999-08-10

    申请人： Randall Richard Good ,  George Everett Foster

    发明人： Randall Richard Good ,  George Everett Foster

    IPC分类号： F01D1100

    CPC分类号： F01D11/122 ,  Y02T50/67 ,  Y02T50/671

    摘要： An air seal is illustrated as used in a gas turbine engine. The seal includes at least a seal substrate, a relatively dense, erosion resistant ceramic layer applied over the bond coat, and an abradable ceramic layer applied in a local area over the dense ceramic layer. The abradable ceramic interacts with a component moving relative to the seal, such as a turbine blade that moves relative to the seal, and cooperates with the moving component to provide sealing and thermal insulation.

    摘要翻译： 示出了在燃气涡轮发动机中使用的空气密封。 该密封件至少包括密封衬底，施加在粘合涂层上的相对致密的耐侵蚀陶瓷层，以及施加在致密陶瓷层上的局部区域中的可磨损陶瓷层。 可磨损陶瓷与相对于密封件移动的部件相互作用，例如相对于密封件移动的涡轮叶片，并与移动部件配合以提供密封和隔热。

    System for cooling turbine blades
    10.
    发明授权
    System for cooling turbine blades 有权
    涡轮叶片冷却系统

    公开(公告)号：US08628299B2

    公开(公告)日：2014-01-14

    申请号：US12691691

    申请日：2010-01-21

    申请人： Luke John Ammann ,  Randall Richard Good

    发明人： Luke John Ammann ,  Randall Richard Good

    IPC分类号： F01D5/18

    CPC分类号： F01D5/20 ,  F01D5/186 ,  F01D5/187 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/67 ,  Y02T50/673 ,  Y02T50/676

    摘要： A system, in one embodiment, includes a turbine blade having a radial blade tip. The system further includes a trailing edge trench that is formed in the radial blade tip and which extends towards a trailing edge of the turbine blade. The trailing edge trench further includes a first set of cooling passages, each of which includes a first slot formed along a first sidewall of the trailing edge trench, whereby the slot is coupled to a first respective hole extending through a floor of the trailing edge trench.

    摘要翻译： 在一个实施例中，系统包括具有径向叶片尖端的涡轮叶片。 该系统还包括形成在径向叶片尖端中并且朝向涡轮叶片的后缘延伸的后缘沟槽。 后缘沟槽还包括第一组冷却通道，每个冷却通道包括沿着后缘沟槽的第一侧壁形成的第一槽，由此所述槽连接到延伸穿过后缘沟槽的底板的第一相应孔 。