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    Cascade impingement cooled airfoil
    2.
    发明申请
    Cascade impingement cooled airfoil 失效
    级联冲击冷却翼型

    公开(公告)号：US20050226726A1

    公开(公告)日：2005-10-13

    申请号：US10820325

    申请日：2004-04-08

    申请人： Ching-Pang Lee ,  Aspi Wadia ,  David Cherry

    发明人： Ching-Pang Lee ,  Aspi Wadia ,  David Cherry

    IPC分类号： F01D5/18 ,  B63H1/14

    CPC分类号： F01D5/187 ,  Y02T50/676

    摘要： A turbine blade includes an airfoil having opposite pressure and suction sidewalls joined together at opposite leading and trailing edges and extending longitudinally from root to tip. A plurality of independent cooling circuits are disposed inside the airfoil correspondingly along the pressure and suction sidewalls thereof. Each circuit includes an inlet channel extending through the dovetail. One of the circuits includes multiple longitudinal channels separated by corresponding perforate partitions each including a row of impingement holes for cascade impingement cooling the inner surface of the airfoil.

    摘要翻译： 涡轮机叶片包括具有相对的压力和抽吸侧壁的翼型件，其在相对的前缘和后缘处连接在一起并且从根部到尖端纵向延伸。 多个独立的冷却回路相应地沿其压力和吸力侧壁设置在翼型内。 每个电路包括延伸穿过燕尾榫的入口通道。 电路中的一个包括由对应的穿孔隔板分开的多个纵向通道，每个隔板包括一排冲击孔，用于级联冲击冷却翼型件的内表面。

    Funnel fillet turbine stage
    3.
    发明申请
    Funnel fillet turbine stage 有权
    漏斗圆角涡轮机阶段

    公开(公告)号：US20060153681A1

    公开(公告)日：2006-07-13

    申请号：US11035866

    申请日：2005-01-10

    申请人： Ching-Pang Lee ,  Jan Schilling ,  Aspi Wadia

    发明人： Ching-Pang Lee ,  Jan Schilling ,  Aspi Wadia

    IPC分类号： F01D5/18

    CPC分类号： F01D5/143 ,  F01D5/145 ,  F05D2240/81 ,  Y02T50/673 ,  Y02T50/676

    摘要： A turbine stage includes a row of airfoils and their platforms spaced laterally apart to define flow passages therebetween. Each airfoil is integrally joined to its platform at a funnel-shaped fillet along the pressure side of the airfoil which decreases in size from the leading edge towards the trailing edge. A field of film cooling holes extends through the platform along the fillet for discharging film cooling air.

    摘要翻译： 涡轮级包括一排翼型件和它们的平台横向间隔开以限定其间的流动通道。 每个翼型件沿着翼型的压力侧以漏斗状的圆角一体地连接到其平台，其尺寸从前缘朝向后缘减小。 膜冷却孔的领域沿着圆角延伸穿过平台以排出膜冷却空气。

    ROTOR STALL SENSOR SYSTEM
    4.
    发明申请
    ROTOR STALL SENSOR SYSTEM 审中-公开
    转子传感器系统

    公开(公告)号：US20100205928A1

    公开(公告)日：2010-08-19

    申请号：US12766413

    申请日：2010-04-23

    申请人： CURTIS W. MOECKEL ,  Aspi Wadia ,  David S. Clark ,  Andrew Breeze-Stringfellow

    发明人： CURTIS W. MOECKEL ,  Aspi Wadia ,  David S. Clark ,  Andrew Breeze-Stringfellow

    IPC分类号： F04D27/00

    CPC分类号： F04D27/001

    摘要： A system for detecting onset of a stall in a rotor is disclosed, the system comprising a sensor spaced radially outwardly and apart from tips of a circumferential row of blades at a location on a static component that is between a first location and a second location wherein the first location is at a first distance of about 25% blade tip-chord length axially forward from the leading edge of a blade and the second location is at a second distance of about 25% blade tip-chord length axially aft from the trailing edge of a blade and wherein the sensor is capable of generating an input signal corresponding to a flow parameter at a location near the tip of a blade and indicative of the onset of a stall and a correlation processor that generates a stability correlation signal.

    摘要翻译： 公开了一种用于检测转子中失速开始的系统，该系统包括传感器，该传感器在位于第一位置和第二位置之间的静态部件上的位置处径向向外并与周向行叶片的尖端分开，其中 第一位置是从叶片的前缘轴向向前的约25％的叶片尖端弦长的第一距离，并且第二位置距离后缘的轴向后方的约25％的叶片尖端弦长的第二距离 并且其中所述传感器能够产生对应于在叶片尖端附近的位置处的流量参数的输入信号，并指示失速的开始以及产生稳定性相关信号的相关处理器。

    METHOD AND APPARATUS FOR REDUCING TURBINE BLADE TEMPERATURES
    7.
    发明申请
    METHOD AND APPARATUS FOR REDUCING TURBINE BLADE TEMPERATURES 失效
    减少涡轮叶片温度的方法和装置

    公开(公告)号：US20070059172A1

    公开(公告)日：2007-03-15

    申请号：US10824283

    申请日：2004-04-14

    申请人： Ching-Pang Lee ,  Aspi Wadia ,  Steven Brassfield

    发明人： Ching-Pang Lee ,  Aspi Wadia ,  Steven Brassfield

    IPC分类号： F01D5/18

    CPC分类号： F01D5/187 ,  Y02T50/676

    摘要： An airfoil for a gas turbine engine includes a first sidewall and a second sidewall coupled together at a leading edge and atrailing edge, such that a cavity is defined therebetween. A plurality of rib walls extends at least partially between the first and second sidewalls, wherein the plurity of rib walls define at least one cooling circuit having at least three cooling chambers. At least one row of openings extend through at least one of the rib walls, wherein a first of cooling chambers supplies cooling fluid to the cavity, and the remaining cooling chambers are coupled in flow communication with the first cooling chamber via the openings.

    摘要翻译： 用于燃气涡轮发动机的翼型件包括在前缘和后缘处联接在一起的第一侧壁和第二侧壁，使得在其间限定空腔。 多个肋壁至少部分地在第一和第二侧壁之间延伸，其中肋壁的柔软度限定了至少一个具有至少三个冷却室的冷却回路。 至少一排开口延伸穿过所述肋壁中的至少一个，其中第一冷却室将冷却流体供应到空腔，并且剩余的冷却室经由所述开口与第一冷却室流动连通地联接。

    PLASMA SENSOR STALL CONTROL SYSTEM AND TURBOMACHINERY DIAGNOSTICS
    9.
    发明申请
    PLASMA SENSOR STALL CONTROL SYSTEM AND TURBOMACHINERY DIAGNOSTICS 审中-公开
    等离子体传感器STALL CONTROL SYSTEM和TURBOMACHINERY DIAGNOSTICS

    公开(公告)号：US20100290906A1

    公开(公告)日：2010-11-18

    申请号：US12766432

    申请日：2010-04-23

    申请人： Curtis W. Moeckel ,  Aspi Wadia ,  David S. Clark ,  Andrew Breeze-Stringfellow

    发明人： Curtis W. Moeckel ,  Aspi Wadia ,  David S. Clark ,  Andrew Breeze-Stringfellow

    IPC分类号： F01D7/00

    CPC分类号： F01D21/003 ,  F01D17/06 ,  F05D2270/101 ,  F05D2270/172

    摘要： A system for detecting onset of a stall in a rotor is disclosed, the system comprising a plasma sensor spaced radially outwardly and apart from tips of a circumferential row of blades at a location on a static component that is between a first location and a second location wherein the first location is at a first distance of about 25% blade tip-chord length axially forward from the leading edge of a blade and the second location is at a second distance of about 25% blade tip-chord length axially aft from the trailing edge of a blade and wherein the plasma sensor is capable of generating an input signal corresponding to a flow parameter at a location near the tip of a blade and indicative of the onset of a stall and a correlation processor that generates a stability correlation signal.

    摘要翻译： 公开了一种用于检测转子中的失速开始的系统，该系统包括等离子体传感器，该等离子体传感器在位于第一位置和第二位置之间的静态部件上的位置处径向向外并与周向行叶片的尖端分开 其中所述第一位置与从叶片的前缘轴向向前的约25％的叶片尖端弦弦长度的第一距离处，并且所述第二位置距离所述拖尾的轴向后方约25％的叶片尖端弦弦长度的第二距离 叶片的边缘，并且其中等离子体传感器能够产生对应于在叶片尖端附近的位置处的流动参数的输入信号，并指示失速的开始以及产生稳定性相关信号的相关处理器。