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    TURBINE BUCKET INTERNAL CORE PROFILE
    1.
    发明申请
    TURBINE BUCKET INTERNAL CORE PROFILE 有权
    TURBINE BUCKET内芯轮廓

    公开(公告)号：US20140069110A1

    公开(公告)日：2014-03-13

    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

    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 internal core profile
    2.
    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
    5.
    发明申请
    TURBINE BUCKET AIRFOIL PROFILE 有权

    公开(公告)号：US20130136610A1

    公开(公告)日：2013-05-30

    申请号：US13304734

    申请日：2011-11-28

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

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

    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.

    Turbine bucket airfoil profile
    6.
    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。

    BUCKET ASSEMBLY FOR TURBOMACHINE
    7.
    发明申请
    BUCKET ASSEMBLY FOR TURBOMACHINE 审中-公开
    用于涡轮发动机的水箱总成

    公开(公告)号：US20140069108A1

    公开(公告)日：2014-03-13

    申请号：US13606404

    申请日：2012-09-07

    申请人： Randall Richard Good ,  Gary Michael Itzel ,  Aaron Ezekiel Smith

    发明人： Randall Richard Good ,  Gary Michael Itzel ,  Aaron Ezekiel Smith

    IPC分类号： F01D5/18

    CPC分类号： F01D5/187

    摘要： Bucket assemblies are provided. The bucket assembly includes a shank, and an airfoil positioned radially outward of the shank. The bucket assembly further includes a main cooling circuit defined in the airfoil and the shank, the main cooling circuit comprising seven passages, each of the seven passages fluidly connected with an adjacent one of the seven passages. A maximum rotation number in each of the seven passages is less than or equal to approximately 0.4.

    摘要翻译： 提供铲斗组件。 铲斗组件包括柄和位于柄的径向外侧的翼型。 铲斗组件还包括限定在翼型件和柄部中的主冷却回路，主冷却回路包括七个通道，七个通道中的每一个与七个通道中的相邻一个流体连接。 七个通道中的每一个中的最大转数小于或等于大约0.4。

    System for cooling turbine blades
    9.
    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 。

    SYSTEM FOR COOLING TURBINE BLADES
    10.
    发明申请
    SYSTEM FOR COOLING TURBINE BLADES 有权
    用于冷却涡轮叶片的系统

    公开(公告)号：US20110176929A1

    公开(公告)日：2011-07-21

    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 。