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    Compound nozzle cooled engine
    41.
    发明授权
    Compound nozzle cooled engine 有权
    复合喷嘴冷却发动机

    公开(公告)号：US07870743B2

    公开(公告)日：2011-01-18

    申请号：US11595669

    申请日：2006-11-10

    Applicant: Ching-Pang Lee ,  Thomas Ory Moniz ,  Robert Joseph Orlando

    Inventor： Ching-Pang Lee ,  Thomas Ory Moniz ,  Robert Joseph Orlando

    IPC: F02C6/08

    CPC classification number: F02C7/12 ,  F01D5/189 ,  F05D2220/3212 ,  F05D2260/201 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. The turbine includes a nozzle followed by a row of rotor blades. A first bleed circuit is joined in flow communication between the last stage of the compressor and a forward cooling channel in vanes of the nozzle for feeding first cooling holes therein with pressurized primary air at a first pressure. A second bleed circuit is joined in flow communication between an intermediate stage of the compressor and aft cooling channels in the nozzle vanes to feed second cooling holes with pressurized secondary air at a second pressure less than the first pressure.

    Abstract translation: 燃气涡轮发动机包括可操作地连接在一起的压缩机，燃烧器和高压涡轮机。 涡轮机包括喷嘴，随后是一排转子叶片。 第一泄放回路在压缩机的最后阶段和喷嘴的叶片中的前冷却通道之间流动连通地连接，用于在第一压力下用加压的一次空气向其中供给第一冷却孔。 第二泄放回路在压缩机的中间级与喷嘴叶片中的后冷却通道之间流动连通地连接，以在小于第一压力的第二压力下用加压的二次空气供给第二冷却孔。

    Reciprocal cooled turbine nozzle
    42.
    发明授权
    Reciprocal cooled turbine nozzle 有权
    往复冷却涡轮喷嘴

    公开(公告)号：US07836703B2

    公开(公告)日：2010-11-23

    申请号：US11765522

    申请日：2007-06-20

    Applicant: Ching-Pang Lee ,  Robert Joseph Orlando

    Inventor： Ching-Pang Lee ,  Robert Joseph Orlando

    IPC: F02C7/12

    CPC classification number: F01D9/041 ,  F01D5/186 ,  F01D5/189 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/67 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A turbine nozzle includes first and second vanes joined to outer and inner bands. The vanes include outboard sides defining outboard flow passages containing axial splitlines, and opposite inboard sides defining an inboard flow passage without axial splitline. The two vanes include different cooling circuits for differently cooling the inboard and outboard vane sides.

    Abstract translation: 涡轮喷嘴包括连接到外带和内带的第一和第二叶片。 叶片包括限定外侧流动通道的外侧面，其包含轴向分裂线，并且相对的内侧限定内侧流动通道而不具有轴向分裂线。 两个叶片包括用于不同地冷却内侧和外侧叶片侧面的不同冷却回路。

    SYSTEM AND METHOD FOR IMPROVED FILM COOLING
    44.
    发明申请
    SYSTEM AND METHOD FOR IMPROVED FILM COOLING 有权
    改进膜片冷却的系统和方法

    公开(公告)号：US20100282721A1

    公开(公告)日：2010-11-11

    申请号：US12435547

    申请日：2009-05-05

    Applicant: Ronald Scott Bunker ,  Wenwu Zhang ,  Wilbur Douglas Scheidt ,  Magdi Naim Azer ,  Marshall Gordon Jones ,  Ching-Pang Lee

    Inventor： Ronald Scott Bunker ,  Wenwu Zhang ,  Wilbur Douglas Scheidt ,  Magdi Naim Azer ,  Marshall Gordon Jones ,  Ching-Pang Lee

    IPC: B23K26/38

    CPC classification number: F01D25/12 ,  B23K26/0624 ,  B23K26/389 ,  F01D25/285 ,  F05D2230/13 ,  F05D2260/202 ,  F05D2260/221 ,  Y02T50/67 ,  Y02T50/672 ,  Y02T50/676

    Abstract: A system for producing at least one trench to improve film cooling in a sample is provided. The system includes at least one laser source outputting at least one pulsed laser beam. The pulsed laser beam includes a pulse duration including a range less than about 50 μs, an energy per pulse having a range less than about 0.1 Joule, and a repetition rate with a range greater than about 1000 Hz. The system also includes a control subsystem coupled to the laser source, the control subsystem configured to synchronize a position of the sample with the pulse duration and energy level in order to selectively remove at least one of a thermal barrier coating, a bondcoat and a substrate metal in the sample to form the at least one trench.

    Abstract translation: 提供一种用于生产至少一个沟槽以改善样品中的膜冷却的系统。 该系统包括输出至少一个脉冲激光束的至少一个激光源。 脉冲激光束包括包括小于约50μs的范围的脉冲持续时间，具有小于约0.1焦耳的范围的每脉冲的能量以及范围大于约1000Hz的重复率。 该系统还包括耦合到激光源的控制子系统，该控制子系统被配置为使样本的位置与脉冲持续时间和能量水平同步，以选择性地去除热障涂层，粘合涂层和基底中的至少一个 金属，以形成至少一个沟槽。

    Plasma lifted boundary layer gas turbine engine vane
    46.
    发明授权
    Plasma lifted boundary layer gas turbine engine vane 有权
    等离子提升边界层燃气轮机发动机叶片

    公开(公告)号：US07766599B2

    公开(公告)日：2010-08-03

    申请号：US11591264

    申请日：2006-10-31

    Applicant: Ching-Pang Lee ,  Aspi Rustom Wadia ,  David Glenn Cherry ,  Je-Chin Han

    Inventor： Ching-Pang Lee ,  Aspi Rustom Wadia ,  David Glenn Cherry ,  Je-Chin Han

    IPC: F01B25/02

    CPC classification number: F01D5/145 ,  F01D9/041 ,  F01D17/162 ,  F05D2260/20 ,  F05D2270/17 ,  F05D2270/172 ,  Y02T50/673 ,  Y02T50/676 ,  Y10S415/914

    Abstract: A plasma boundary layer lifting system includes at least one gas turbine engine vane having a spanwise extending airfoil with an outer surface extending in a chordwise direction between opposite leading and trailing edges and chordwise spaced apart plasma generators for producing a plasma extending in the chordwise direction along the outer surface. Each plasma generator may include inner and outer electrodes separated by a dielectric material disposed within a spanwise extending groove in the outer surface. The airfoil may be hollow having an outer wall and the plasma generators being mounted on the outer wall. A method for operating the system includes forming a plasma extending in the chordwise direction along the outer surface of the airfoil. The method may further include operating the plasma generators in steady state or unsteady modes.

    Abstract translation: 等离子体边界层提升系统包括至少一个燃气涡轮发动机叶片，其具有翼展方向延伸的翼型件，其外表面沿相反的前缘和后缘之间的弦向延伸，以及弦向间隔开的等离子体发生器，用于产生沿着弦方向延伸的等离子体 外表面。 每个等离子体发生器可以包括由设置在外表面中的翼展方向延伸凹槽内的电介质材料隔开的内电极和外电极。 翼型件可以是中空的，具有外壁，等离子体发生器安装在外壁上。 用于操作该系统的方法包括形成沿着翼型的外表面沿着弦方向延伸的等离子体。 该方法还可以包括以稳态或不稳定模式操作等离子体发生器。

    Compound turbine cooled engine
    47.
    发明授权
    Compound turbine cooled engine 有权
    复合涡轮冷却发动机

    公开(公告)号：US07743613B2

    公开(公告)日：2010-06-29

    申请号：US11595668

    申请日：2006-11-10

    Applicant: Ching-Pang Lee ,  Thomas Ory Moniz ,  Robert Joseph Orlando

    Inventor： Ching-Pang Lee ,  Thomas Ory Moniz ,  Robert Joseph Orlando

    IPC: F02C6/08

    CPC classification number: F01D9/065 ,  F01D25/12 ,  F02C7/12 ,  Y02T50/671 ,  Y02T50/675

    Abstract: A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. The turbine includes a row of nozzle vanes followed by a row of rotor blades. The vanes and blades have corresponding forward and aft internal cooling channels. First, second, third, and fourth bleed circuits are joined in flow communication with different stages of the compressor for bleeding pressurized air therefrom at different pressures to provide coolant to the forward and aft channels of the turbine vanes and blades.

    Abstract translation: 燃气涡轮发动机包括可操作地连接在一起的压缩机，燃烧器和高压涡轮机。 涡轮机包括一排喷嘴叶片，随后是一排转子叶片。 叶片和叶片具有相应的前后冷却通道。 第一，第二，第三和第四泄放回路与压缩机的不同级联流动连通，以在不同压力下从其中排出加压空气，以向涡轮机叶片和叶片的前后通道提供冷却剂。

    Methods and system for cooling integral turbine nozzle and shroud assemblies
    48.
    发明授权
    Methods and system for cooling integral turbine nozzle and shroud assemblies 失效
    冷却整体涡轮喷嘴和护罩组件的方法和系统

    公开(公告)号：US07740442B2

    公开(公告)日：2010-06-22

    申请号：US11565447

    申请日：2006-11-30

    Applicant: Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Daniel Verner Jones

    Inventor： Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Daniel Verner Jones

    IPC: F01D25/12

    CPC classification number: F01D9/04 ,  F05D2240/80 ,  F05D2260/201 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/005 ,  F23R3/06 ,  F23R2900/03044 ,  Y02T50/671 ,  Y02T50/676

    Abstract: A method for cooling a shroud segment of a gas turbine engine includes providing a turbine shroud assembly including a shroud segment having a leading edge defining a forward face. A turbine nozzle is coupled to the turbine shroud assembly such that a gap is defined between an aft face of an outer band of the turbine nozzle and the forward face, wherein a lip formed on the aft face is positioned radially inwardly with respect to the gap and extends substantially axially downstream from the gap. Cooling air is directed into the gap. Cooling air exiting the gap impinges against the lip to facilitate film cooling the shroud segment.

    Abstract translation: 一种用于冷却燃气涡轮发动机的护罩区段的方法包括提供一种涡轮机护罩组件，其包括具有限定前表面的前缘的护罩区段。 涡轮喷嘴联接到涡轮机护罩组件，使得在涡轮喷嘴的外带的前表面和前表面之间限定间隙，其中形成在后表面上的唇缘相对于间隙径向向内定位 并且从所述间隙基本轴向地延伸到下游。 冷却空气被引导到间隙中。 离开间隙的冷却空气撞击唇缘，以便薄膜冷却护罩段。

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