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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。

    Methods and apparatus for cooling gas turbine engine blade tips
    9.
    发明授权
    Methods and apparatus for cooling gas turbine engine blade tips 有权
    用于冷却燃气涡轮发动机叶片尖端的方法和装置

    公开(公告)号：US06431820B1

    公开(公告)日：2002-08-13

    申请号：US09796967

    申请日：2001-02-28

    申请人： Robert John Beacock ,  Omer Duane Erdmann ,  Robert Edward Athans ,  Harold Paul Rieck, Jr.

    发明人： Robert John Beacock ,  Omer Duane Erdmann ,  Robert Edward Athans ,  Harold Paul Rieck, Jr.

    IPC分类号： F01D906

    CPC分类号： F01D5/188 ,  F01D9/041 ,  F01D25/12 ,  F05D2260/201 ,  F05D2260/205 ,  Y02T50/671 ,  Y02T50/676

    摘要： A turbine for a gas turbine engine including a turbine nozzle assembly that facilitates reducing an operating temperature of rotor blades in a cost-effective and reliable manner is described. Each rotor blade includes a tip that rotates in close proximity to a shroud that extends circumferentially around the rotor assembly. The turbine nozzle assembly includes a plurality of turbine vane segments that channel combustion gases to downstream rotor blades. Each turbine vane segment extends radially outward from an inner platform and includes a tip, a root, and a body that extends therebetween. The turbine vane segment tip is formed integrally with an outer band that mounts the vane segments within the gas turbine engine. The outer band is in flow communication with a cooling fluid source, and includes at least one opening.

    摘要翻译： 描述了一种用于燃气涡轮发动机的涡轮机，其包括涡轮喷嘴组件，其有助于以成本有效且可靠的方式降低转子叶片的操作温度。 每个转子叶片包括尖端，该尖端沿着围绕转子组件周向延伸的护罩紧密地旋转。 涡轮喷嘴组件包括多个涡轮叶片段，其将燃烧气体引导到下游转子叶片。 每个涡轮叶片段从内平台径向向外延伸，并包括在其间延伸的尖端，根部和本体。 涡轮叶片节段末端与将叶片段安装在燃气涡轮发动机内的外带一体地形成。 外带与冷却流体源流动连通，并且包括至少一个开口。