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    Method and apparatus for non-parallel turbine dovetail-faces
    4.
    发明授权
    Method and apparatus for non-parallel turbine dovetail-faces 有权
    非平行涡轮燕尾面的方法和装置

    公开(公告)号：US06592330B2

    公开(公告)日：2003-07-15

    申请号：US09943528

    申请日：2001-08-30

    申请人： Leslie Eugene Leeke ,  Sean Robert Keith ,  Ronald Eugene Mc Rae, Jr. ,  Robert Ingram Ackerman ,  Richard William Albrecht, Jr.

    发明人： Leslie Eugene Leeke ,  Sean Robert Keith ,  Ronald Eugene Mc Rae, Jr. ,  Robert Ingram Ackerman ,  Richard William Albrecht, Jr.

    IPC分类号： F03B314

    CPC分类号： F01D5/3007 ,  Y10T29/49321

    摘要： A dovetail assembly including non-parallel relief faces that facilitates reduced pressure face brinelling in turbine engines. The assembly includes a plurality of rotor blades, each including a dovetail. Each dovetail includes at least a pair of blade tangs including blade relief faces. The dovetail assembly also includes a rotor disk including a plurality of dovetail slots, each sized to receive a dovetail. Each dovetail slot is defined by at least one pair of opposing disk tangs including disk relief faces. The disk relief faces are non-parallel to the blade relief faces when the dovetail is mounted in the dovetail slot.

    摘要翻译： 燕尾组件包括不平行的浮雕面，其有利于在涡轮发动机中降低压力。 组件包括多个转子叶片，每个转子叶片包括燕尾形。 每个燕尾榫至少包括一对刀片，包括刀片浮雕面。 燕尾组件还包括转子盘，该转子盘包括多个燕尾槽，每个燕尾槽的尺寸被设计成接纳燕尾。 每个燕尾槽由至少一对相对的盘形凸起限定，包括盘浮雕面。 当燕尾榫安装在燕尾槽中时，盘浮雕面不平行于刀片浮雕面。

    Step-down turbine platform
    5.
    发明授权
    Step-down turbine platform 有权
    降压式涡轮平台

    公开(公告)号：US06672832B2

    公开(公告)日：2004-01-06

    申请号：US10040660

    申请日：2002-01-07

    申请人： Leslie Eugene Leeke ,  Sean Robert Keith ,  Lawrence Paul Timko

    发明人： Leslie Eugene Leeke ,  Sean Robert Keith ,  Lawrence Paul Timko

    IPC分类号： F01D530

    CPC分类号： F01D5/143 ,  Y02T50/673 ,  Y10S415/914

    摘要： A turbine includes a row of blades each having an integral airfoil, platform, and dovetail. Each platform has opposite first and second side edges corresponding with the opposite pressure and suction sides of the airfoil. The platform first side edge is radially higher than the platform second side edge continuously between opposite forward and aft edges of the platform. In this way, adjacent platforms define a down step therebetween for preventing obstruction of combustion gases flowable downstream thereover.

    摘要翻译： 涡轮机包括一排叶片，每排叶片具有整体的翼型，平台和燕尾榫。 每个平台具有相对的第一和第二侧边缘对应于翼型的相对的压力和抽吸侧。 平台第一侧边缘在平台的相对的前后边缘之间连续地径向地高于平台第二侧边缘。 以这种方式，相邻的平台在其间限定了一个向下的步骤，用于防止在其下游流动的燃烧气体的阻塞。

    Turbine rotor blade assembly and method of assembling the same
    9.
    发明授权
    Turbine rotor blade assembly and method of assembling the same 有权
    涡轮转子叶片组件及其组装方法

    公开(公告)号：US07878763B2

    公开(公告)日：2011-02-01

    申请号：US11748529

    申请日：2007-05-15

    申请人： Sean Robert Keith ,  Michael Joseph Danowski ,  Leslie Eugene Leeke, Jr.

    发明人： Sean Robert Keith ,  Michael Joseph Danowski ,  Leslie Eugene Leeke, Jr.

    IPC分类号： F01D5/30

    CPC分类号： F01D5/3007 ,  F01D5/147 ,  F01D11/008 ,  F05D2230/60 ,  F05D2240/80 ,  Y10T29/49336

    摘要： A removable rotor blade platform includes a first platform leg, a second platform leg, and a platform portion coupled to the first and second platform legs. The first platform leg is configured to be retained by a first retainer coupled to a first rotor blade, and the second platform leg is configured to be retained by a second retainer coupled to a second adjacent rotor blade. A method of assembling a blade assembly that includes a removable platform, a rotor assembly including the removable platform, and a gas turbine engine assembly including the removable platform, are also described herein.

    摘要翻译： 可移动的转子叶片平台包括第一平台腿，第二平台腿和联接到第一和第二平台腿的平台部分。 第一平台腿被构造成由联接到第一转子叶片的第一保持器保持，并且第二平台腿被构造成由联接到第二相邻转子叶片的第二保持器保持。 本文还描述了组装包括可拆卸平台的叶片组件的方法，包括可移除平台的转子组件和包括可移除平台的燃气涡轮发动机组件。