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6 条记录 (耗时 0.025 秒)

    Plasma Clearance Controlled Compressor
    2.
    发明申请
    Plasma Clearance Controlled Compressor 审中-公开
    等离子体间隙控制压缩机

    公开(公告)号：US20100284795A1

    公开(公告)日：2010-11-11

    申请号：US11966309

    申请日：2007-12-28

    申请人： Aspi Rustom Wadia ,  David Scott Clark ,  Ching-Pang Lee ,  Andrew Breeze-Stringfellow ,  Gregory Scott McNulty

    发明人： Aspi Rustom Wadia ,  David Scott Clark ,  Ching-Pang Lee ,  Andrew Breeze-Stringfellow ,  Gregory Scott McNulty

    IPC分类号： F01D11/08

    CPC分类号： F01D11/20 ,  F05D2270/172

    摘要： A plasma leakage flow control system for a compressor is disclosed, comprising a circumferential row of compressor blades, an annular casing surrounding the tips of the blades, located radially apart from the tips of the blades and at least one annular plasma generator located on the annular casing. The annular plasma generator comprises an inner electrode and an outer electrode separated by a dielectric material. A gas turbine engine having a plasma leakage flow control system further comprises an engine control system which controls the operation of the annular plasma generator such that the blade tip leakage flow can be changed.

    摘要翻译： 公开了一种用于压缩机的等离子体泄漏流量控制系统，包括圆周排的压缩机叶片，围绕叶片尖端的环形壳体，位于与叶片的尖端径向分开的位置以及至少一个环形等离子体发生器，其位于环形 套管。 环形等离子体发生器包括由电介质材料隔开的内电极和外电极。 具有等离子体泄漏流量控制系统的燃气涡轮发动机还包括发动机控制系统，其控制环形等离子体发生器的操作，使得可以改变叶片尖端泄漏流。

    Plasma Enhanced Compressor
    4.
    发明申请
    Plasma Enhanced Compressor 审中-公开
    等离子增压压缩机

    公开(公告)号：US20100047060A1

    公开(公告)日：2010-02-25

    申请号：US11966275

    申请日：2007-12-28

    申请人： Aspi Rustom Wadia ,  David Scott Clark ,  Ching-Pang Lee ,  Andrew Breeze-Stringfellow ,  Gregory Scott McNulty

    发明人： Aspi Rustom Wadia ,  David Scott Clark ,  Ching-Pang Lee ,  Andrew Breeze-Stringfellow ,  Gregory Scott McNulty

    IPC分类号： F02C9/16

    CPC分类号： F04D29/526 ,  F05D2270/101 ,  F05D2270/172 ,  F15D1/12

    摘要： A gas turbine engine is disclosed, comprising a compressor having a circumferential row of blades, a casing surrounding the tips of the blades, located radially apart from the tips of the blades and at least one plasma generator located on the casing. The plasma generator comprises a first electrode and a second electrode separated by a dielectric material. The gas turbine engine further comprises an engine control system which controls the operation of the plasma generator such that the stable operating range of the compressor is increased.

    摘要翻译： 公开了一种燃气涡轮发动机，其包括具有周向排的叶片的压缩机，围绕叶片的尖端的壳体，位于与叶片的尖端径向分开的位置以及位于壳体上的至少一个等离子体发生器。 等离子体发生器包括由电介质材料隔开的第一电极和第二电极。 燃气涡轮发动机还包括发动机控制系统，其控制等离子体发生器的操作，使得压缩机的稳定工作范围增加。

    Methods and apparatus for improving engine operation
    6.
    发明授权
    Methods and apparatus for improving engine operation 有权
    改善发动机运行的方法和装置

    公开(公告)号：US06568909B2

    公开(公告)日：2003-05-27

    申请号：US09964019

    申请日：2001-09-26

    申请人： Peter Nicholas Szucs ,  Gregory Scott McNulty ,  Syed Arif Khalid ,  David William Crall

    发明人： Peter Nicholas Szucs ,  Gregory Scott McNulty ,  Syed Arif Khalid ,  David William Crall

    IPC分类号： F01D520

    CPC分类号： F01D5/20 ,  Y10T29/49336

    摘要： An airfoil for a gas turbine engine includes a leading edge, a trailing edge, a tip plate, a first sidewall, and a second sidewall. The first sidewall extends in radial span between an airfoil root and the tip plate. Furthermore, the first sidewall defines a pressure side of the airfoil. The second sidewall is connected to the first sidewall at the leading and trailing edges, and extends in radial span between the airfoil root and the tip plate. The second sidewall defines a suction side of the airfoil. The tip plate includes at least one groove that extends substantially between the first and second sidewalls.

    摘要翻译： 用于燃气涡轮发动机的翼型件包括前缘，后缘，顶板，第一侧壁和第二侧壁。 第一侧壁在翼型根和尖端板之间沿径向间隔延伸。 此外，第一侧壁限定翼型的压力侧。 第二侧壁在前缘和后缘处连接到第一侧壁，并且在翼型根和尖端板之间以径向跨度延伸。 第二侧壁限定翼型的吸力侧。 顶板包括至少一个在第一和第二侧壁之间大致延伸的凹槽。