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    Turbine assembly for a gas turbine engine and method of manufacturing the same
    1.
    发明授权
    Turbine assembly for a gas turbine engine and method of manufacturing the same 有权
    用于燃气涡轮发动机的涡轮组件及其制造方法

    公开(公告)号：US07758306B2

    公开(公告)日：2010-07-20

    申请号：US11615514

    申请日：2006-12-22

    申请人： Scott Andrew Burton ,  Chander Prakash ,  Joseph Machnaim ,  David Glenn Cherry ,  Robert John Beacock ,  Ching-Pang Lee ,  Scott Michael Carson

    发明人： Scott Andrew Burton ,  Chander Prakash ,  Joseph Machnaim ,  David Glenn Cherry ,  Robert John Beacock ,  Ching-Pang Lee ,  Scott Michael Carson

    IPC分类号： F01D1/02

    CPC分类号： F01D9/041 ,  F01D5/141 ,  F01D5/145 ,  Y02T50/673 ,  Y10T29/49236

    摘要： A turbine assembly for a gas turbine engine. The turbine assembly includes at least one stator assembly including a radially inner band and at least one stator vane that extends radially outward from the inner band. The stator vane includes an airfoil having a root portion adjacent to the inner band and a tip portion. The airfoil also includes at least one lean directional change that is defined between the root portion and the tip portion. The turbine assembly also includes at least one turbine blade assembly that includes at least one rotor blade. The blade assembly is coupled in flow communication with the stator assembly such that an axial spacing is defined therebetween. The axial spacing defined adjacent to the at least one lean directional change is wider than the axial spacing defined adjacent to the root portion.

    摘要翻译： 一种用于燃气涡轮发动机的涡轮组件。 涡轮机组件包括至少一个定子组件，其包括径向内部带和至少一个定子叶片，其从内部带径向向外延伸。 定子叶片包括具有与内带相邻的根部部分和尖端部分的翼型件。 翼型件还包括限定在根部部分和尖端部分之间的至少一个精简方向变化。 涡轮组件还包括至少一个包括至少一个转子叶片的涡轮叶片组件。 叶片组件与定子组件流体连通地联接，使得在它们之间限定轴向间隔。 与所述至少一个瘦方向变化相邻限定的轴向间隔比邻近根部限定的轴向间隔宽。

    TURBINE ASSEMBLY FOR A GAS TURBINE ENGINE AND METHOD OF MANUFACTURING THE SAME
    4.
    发明申请
    TURBINE ASSEMBLY FOR A GAS TURBINE ENGINE AND METHOD OF MANUFACTURING THE SAME 有权
    用于气体涡轮发动机的涡轮组件及其制造方法

    公开(公告)号：US20080148564A1

    公开(公告)日：2008-06-26

    申请号：US11615514

    申请日：2006-12-22

    申请人： Scott Andrew Burton ,  Chander Prakash ,  Joseph Machnaim ,  David Glenn Cherry ,  Robert John Beacock ,  Ching-Pang Lee ,  Scott Michael Carson

    发明人： Scott Andrew Burton ,  Chander Prakash ,  Joseph Machnaim ,  David Glenn Cherry ,  Robert John Beacock ,  Ching-Pang Lee ,  Scott Michael Carson

    IPC分类号： F01D5/02

    CPC分类号： F01D9/041 ,  F01D5/141 ,  F01D5/145 ,  Y02T50/673 ,  Y10T29/49236

    摘要： A turbine assembly for a gas turbine engine. The turbine assembly includes at least one stator assembly including a radially inner band and at least one stator vane that extends radially outward from the inner band. The stator vane includes an airfoil having a root portion adjacent to the inner band and a tip portion. The airfoil also includes at least one lean directional change that is defined between the root portion and the tip portion. The turbine assembly also includes at least one turbine blade assembly that includes at least one rotor blade. The blade assembly is coupled in flow communication with the stator assembly such that an axial spacing is defined therebetween. The axial spacing defined adjacent to the at least one lean directional change is wider than the axial spacing defined adjacent to the root portion.

    摘要翻译： 一种用于燃气涡轮发动机的涡轮组件。 涡轮机组件包括至少一个定子组件，其包括径向内部带和至少一个定子叶片，其从内部带径向向外延伸。 定子叶片包括具有与内带相邻的根部部分和尖端部分的翼型件。 翼型件还包括限定在根部部分和尖端部分之间的至少一个精简方向变化。 涡轮组件还包括至少一个包括至少一个转子叶片的涡轮叶片组件。 叶片组件与定子组件流体连通地联接，使得在它们之间限定轴向间隔。 与所述至少一个瘦方向变化相邻限定的轴向间隔比邻近根部限定的轴向间隔宽。

    Turbine blade having angled squealer tip
    10.
    发明授权
    Turbine blade having angled squealer tip 有权
    涡轮叶片具有倾斜的尖叫尖端

    公开(公告)号：US06672829B1

    公开(公告)日：2004-01-06

    申请号：US10196623

    申请日：2002-07-16

    申请人： David Glenn Cherry ,  Ching-Pang Lee ,  Chander Prakash ,  Aspi Rustom Wadia ,  Brian David Keith ,  Steven Robert Brassfield

    发明人： David Glenn Cherry ,  Ching-Pang Lee ,  Chander Prakash ,  Aspi Rustom Wadia ,  Brian David Keith ,  Steven Robert Brassfield

    IPC分类号： F01D518

    CPC分类号： F01D5/141 ,  F01D5/145 ,  F01D5/20 ,  F05D2250/292

    摘要： A turbine blade for a gas turbine engine, including an airfoil and integral dovetail for mounting the airfoil along a radial axis to a rotor disk inboard of a turbine shroud. The airfoil further includes: first and second sidewalls joined together at a leading edge and a trailing edge, where the first and second sidewalls extend from a root disposed adjacent the dovetail to a tip plate for channeling combustion gases thereover; and, at least one tip rib extending outwardly from the tip plate between the leading and trailing edges. The tip rib is oriented so that an axis extending longitudinally therethrough is at an angle with respect to the radial axis for at least a designated portion of an axial length of the turbine blade. Such angle may be substantially the same across the designated portion or may vary thereacross. Accordingly, a recirculation zone of the combustion gases is formed adjacent a distal end of the tip rib which reduces a leakage flow of the combustion gases between the airfoil and the shroud for at least the designated portion of an axial length of the turbine blade.

    摘要翻译： 一种用于燃气涡轮发动机的涡轮机叶片，包括翼型件和整体式燕尾榫，用于将翼型件沿着径向轴线安装到涡轮机外罩内侧的转子盘。 所述翼型件还包括：在前缘和后缘处连接在一起的第一和第二侧壁，其中所述第一和第二侧壁从邻近所述燕尾榫设置的根部延伸到顶板，用于在其上引导燃烧气体; 以及在前缘和后缘之间从顶板向外延伸的至少一个尖端肋。 尖端肋被定向成使得纵向延伸通过的轴线相对于径向轴线成一定角度，用于涡轮叶片的至少一个轴向长度的指定部分。 这种角度在指定部分可以是基本相同的，或者可以在其上变化。 因此，燃烧气体的再循环区域形成在尖端肋的远端附近，这减少了涡轮叶片至少轴向长度的指定部分的翼型和护罩之间的燃烧气体的泄漏流。