利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

11 条记录 (耗时 0.019 秒)

    Blade/disk dovetail backcut for blade/disk stress reduction (6FA and 6FA+e, stage 1)
    1.
    发明授权
    Blade/disk dovetail backcut for blade/disk stress reduction (6FA and 6FA+e, stage 1) 有权
    刀片/盘鸠尾刀片刀片/盘片压力降低（6FA和6FA + e，阶段1）

    公开(公告)号：US07476084B1

    公开(公告)日：2009-01-13

    申请号：US11476096

    申请日：2006-06-28

    申请人： Sze Bun Brian Chan ,  Babu Santhana Gopalakrishnan ,  William Scott Zemitis

    发明人： Sze Bun Brian Chan ,  Babu Santhana Gopalakrishnan ,  William Scott Zemitis

    IPC分类号： F01D5/30

    CPC分类号： F01D5/3007 ,  F01D5/147 ,  F05D2230/10 ,  F05D2240/80 ,  F05D2260/94 ,  F05D2260/941

    摘要： Blade load path on a gas turbine disk can be diverted to provide a significant disk fatigue life benefit. A plurality of gas turbine blades are attachable to a gas turbine disk, where each of the gas turbine blades includes a blade dovetail engageable in a correspondingly-shaped dovetail slot in the gas turbine disk. In order to reduce gas turbine disk stress, an optimal material removal area is defined according to blade and/or disk geometry to maximize a balance between stress reduction on the gas turbine disk, a useful life of the gas turbine blade, and maintaining or improving the aeromechanical behavior of the gas turbine blade. Removing material from the material removal area effects the maximized balance.

    摘要翻译： 可以转向燃气轮机盘上的叶片负载路径以提供显着的盘疲劳寿命益处。 多个燃气轮机叶片可附接到燃气涡轮盘，其中每个燃气轮机叶片包括可接合在燃气涡轮盘中的相应形状的燕尾槽中的叶片燕尾榫。 为了减少燃气轮机盘应力，根据叶片和/或盘几何形状来定义最佳材料去除面积，以最大化燃气轮机盘上的应力减小，燃气轮机叶片的使用寿命和维持或改进之间的平衡 燃气轮机叶片的机械性能。 从材料去除区域去除材料会最大化平衡。

    Turbine assembly
    3.
    发明授权
    Turbine assembly 有权
    涡轮总成

    公开(公告)号：US09151167B2

    公开(公告)日：2015-10-06

    申请号：US13370949

    申请日：2012-02-10

    申请人： William Scott Zemitis ,  Christopher Michael Penny

    发明人： William Scott Zemitis ,  Christopher Michael Penny

    IPC分类号： F01D17/00 ,  F01D5/30 ,  F01D5/26

    CPC分类号： F01D5/3007 ,  F01D5/26

    摘要： According to one aspect of the invention, a turbine assembly includes an airfoil extending from a blade and a dovetail located on a lower portion of the blade, wherein the dovetail has a dovetail contact surface. The turbine assembly also includes a member with a slot configured to couple to the airfoil via the dovetail, the slot having a slot contact surface to contact the dovetail contact surface, wherein the dovetail contact surface is reduced by a relief to alter a fundamental frequency of an assembly of the blade and member.

    摘要翻译： 根据本发明的一个方面，涡轮组件包括从叶片延伸的翼型件和位于叶片下部的燕尾榫，其中燕尾榫具有燕尾接触表面。 涡轮机组件还包括具有狭槽的构件，槽被配置成经由燕尾形件连接到翼型件，该槽具有接触燕尾接触表面的槽接触表面，其中燕尾接触表面被减压以改变基部频率 叶片和构件的组件。

    Turbine bucket airfoil profile
    4.
    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。

    Blade/disk dovetail backcut for blade/disk stress reduction (7FA+e, stage 2)
    5.
    发明授权
    Blade/disk dovetail backcut for blade/disk stress reduction (7FA+e, stage 2) 有权
    刀片/圆盘燕尾刀后刀刃/盘减少压力（7FA + e，阶段2）

    公开(公告)号：US07419361B1

    公开(公告)日：2008-09-02

    申请号：US11476108

    申请日：2006-06-28

    申请人： Steve Paul Byam ,  William Scott Zemitis

    发明人： Steve Paul Byam ,  William Scott Zemitis

    IPC分类号： F01D5/30

    CPC分类号： F01D5/3007 ,  F01D5/147 ,  F05D2230/10 ,  F05D2240/81 ,  F05D2260/941

    摘要： Blade load path on a gas turbine disk can be diverted to provide a significant disk fatigue life benefit. A plurality of gas turbine blades are attachable to a gas turbine disk, where each of the gas turbine blades includes a blade dovetail engageable in a correspondingly-shaped dovetail slot in the gas turbine disk. In order to reduce gas turbine disk stress, an optimal material removal area is defined according to blade and/or disk geometry to maximize a balance between stress reduction on the gas turbine disk, a useful life of the gas turbine blade, and maintaining or improving the aeromechanical behavior of the gas turbine blade. Removing material from the material removal area effects the maximized balance.

    摘要翻译： 可以转向燃气轮机盘上的叶片负载路径以提供显着的盘疲劳寿命益处。 多个燃气轮机叶片可附接到燃气涡轮盘，其中每个燃气轮机叶片包括可接合在燃气涡轮盘中的相应形状的燕尾槽中的叶片燕尾榫。 为了减少燃气轮机盘应力，根据叶片和/或盘几何形状来定义最佳材料去除面积，以最大化燃气轮机盘上的应力减小，燃气轮机叶片的使用寿命和维持或改进之间的平衡 燃气轮机叶片的机械性能。 从材料去除区域去除材料会最大化平衡。

    TURBINE ASSEMBLY
    6.
    发明申请
    TURBINE ASSEMBLY 有权
    涡轮总成

    公开(公告)号：US20130209253A1

    公开(公告)日：2013-08-15

    申请号：US13370949

    申请日：2012-02-10

    申请人： William Scott Zemitis ,  Christopher Michael Penny

    发明人： William Scott Zemitis ,  Christopher Michael Penny

    IPC分类号： F01D17/00 ,  F01D5/30

    CPC分类号： F01D5/3007 ,  F01D5/26

    摘要： According to one aspect of the invention, a turbine assembly includes an airfoil extending from a blade and a dovetail located on a lower portion of the blade, wherein the dovetail has a dovetail contact surface. The turbine assembly also includes a member with a slot configured to couple to the airfoil via the dovetail, the slot having a slot contact surface to contact the dovetail contact surface, wherein the dovetail contact surface is reduced by a relief to alter a fundamental frequency of an assembly of the blade and member.

    摘要翻译： 根据本发明的一个方面，涡轮组件包括从叶片延伸的翼型件和位于叶片下部的燕尾榫，其中燕尾榫具有燕尾接触表面。 涡轮机组件还包括具有狭槽的构件，槽被配置成经由燕尾形件连接到翼型件，该槽具有接触燕尾接触表面的槽接触表面，其中燕尾接触表面被减压以改变基部频率 叶片和构件的组件。

    Turbine bucket airfoil profile
    9.
    发明授权
    Turbine bucket airfoil profile 有权
    涡轮斗翼型材

    公开(公告)号：US09011101B2

    公开(公告)日：2015-04-21

    申请号：US13304743

    申请日：2011-11-28

    申请人： Ross James Gustafson ,  Christopher Michael Penny ,  Aaron Ezekiel Smith ,  Luke C Sponsellar ,  William Scott Zemitis

    发明人： Ross James Gustafson ,  Christopher Michael Penny ,  Aaron Ezekiel Smith ,  Luke C Sponsellar ,  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。