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    FAN STALL DETECTION SYSTEM
    1.
    发明申请
    FAN STALL DETECTION SYSTEM 审中-公开
    风扇检测系统

    公开(公告)号：WO2011133293A1

    公开(公告)日：2011-10-27

    申请号：PCT/US2011/030151

    申请日：2011-03-28

    Applicant: GENERAL ELECTRIC COMPANY ,  MOECKEL, Curtis, W. ,  WADIA, Aspi ,  CLARK, David, S. ,  BREEZE-STRINGFELLOW, Andrew

    Inventor： MOECKEL, Curtis, W. ,  WADIA, Aspi ,  CLARK, David, S. ,  BREEZE-STRINGFELLOW, Andrew

    IPC: F04D27/02 ,  G05B19/048

    CPC classification number: G05B19/048 ,  F04D27/001

    Abstract: A system (500) for detecting onset of a stall in a rotor is disclosed, the system comprising a sensor (502,60) spaced radially outwardly and apart from tips (46) of a circumferential row of blades (47) at a location on a static component 50 that is between a first location (57) and a second location (58) wherein the first location (57) is at a first distance (157) of about 25% blade tip-chord length (49) axially forward from the leading edge (41) of a blade (47) and the second location (58) is at a second distance (158) of about 25% blade tip-chord length (49) axially aft from the trailing edge (42) of a blade (47) and wherein the sensor (502, 60) is capable of generating an input signal (504) corresponding to a flow parameter at a location (52) near the tip (46) of a blade (40) and indicative of the onset of a stall. The system further comprises a control system (74) capable of generating a rotor speed signal (506) and a correlation processor (510) capable of receiving the input signal (504) ant the rotor speed signal (506) wherein the correlation processor generates stability correlation signal (512).

    Abstract translation: 公开了一种用于检测转子中失速开始的系统（500），该系统包括一个传感器（502,60），该传感器（502,60）在周向排的叶片（47）的位置处径向向外和与头部（46）分开， 位于第一位置（57）和第二位置（58）之间的静态部件50，其中所述第一位置（57）处于从所述第一位置（57）轴向向前延伸约25％的叶片尖端弦长（49）的第一距离（157） 叶片（47）的前缘（41）和第二位置（58）处于距离叶片（47）的后缘（42）的轴向后方约25％的叶片尖端弦长度（49）的第二距离（158） 叶片（47），并且其中所述传感器（502,60）能够产生对应于在叶片（40）的尖端（46）附近的位置（52）处的流动参数的输入信号（504），并且指示 发生失速 该系统还包括能够产生转子速度信号（506）的控制系统（74）和能够接收转子速度信号（506）的输入信号（504）的相关处理器（510），其中相关处理器产生稳定性 相关信号（512）。

    HIGH CAMBER COMPRESSOR ROTOR BLADE
    7.
    发明申请
    HIGH CAMBER COMPRESSOR ROTOR BLADE 审中-公开
    高档压缩机转子叶片

    公开(公告)号：WO2012134833A3

    公开(公告)日：2013-02-14

    申请号：PCT/US2012029357

    申请日：2012-03-16

    Applicant: GEN ELECTRIC ,  BEACHER BRENT FRANKLIN ,  CLARK DAVID SCOTT ,  BREEZE-STRINGFELLOW ANDREW

    Inventor： BEACHER BRENT FRANKLIN ,  CLARK DAVID SCOTT ,  BREEZE-STRINGFELLOW ANDREW

    IPC: F04D29/32 ,  F01D5/14

    CPC classification number: F04D29/324 ,  F01D5/141 ,  Y02T50/673

    Abstract: A rotor blade (104) having an airfoil (10) for a compressor is described. The airfoil has an airfoil root (11), an airfoil tip (12) located at a spanwise distance from the airfoil root, a leading edge (20) extending from the airfoil root to the airfoil tip, an inner span region (13, S2) between the airfoil root and a first height location (41) on the airfoil leading edge, a midspan region (23, S2) between the first height location and a second height location (42) on the airfoil leading edge located radially outward from the first height location; an outer span region (14, S3) between the second height location and the airfoil tip, wherein the airfoil has a normalized camber profile (120) such that the normalized camber increases in the outer span region in a spanwise direction towards the tip and is more than 2.2 in the outer span region.

    Abstract translation: 描述了具有用于压缩机的翼型件（10）的转子叶片（104）。 所述翼型件具有翼型根部（11），位于与翼型根部翼展距离的翼型件（12），从所述翼型件根部延伸到所述翼型件前端的前缘（20），内跨距区域（13，S2 ）在所述翼型件前缘和所述翼型件前缘之间的第一高度位置（41）之间，在所述第一高度位置与所述翼型件前缘之间的第二高度位置（42）之间的中跨区域（23，S2） 第一高度位置; 在所述第二高度位置和所述翼型端之间的外跨距区域（14,3S），其中所述翼型件具有归一化的弧形轮廓（120），使得所述标准化的外倾角在所述外跨距区域沿翼展方向朝向所述尖端增加，并且是 在外跨区域超过2.2。

    HIGH CAMBER COMPRESSOR ROTOR BLADE
    9.
    发明申请
    HIGH CAMBER COMPRESSOR ROTOR BLADE 审中-公开
    高档压缩机转子叶片

    公开(公告)号：WO2012134833A2

    公开(公告)日：2012-10-04

    申请号：PCT/US2012/029357

    申请日：2012-03-16

    Applicant: GENERAL ELECTRIC COMPANY ,  BEACHER, Brent, Franklin ,  CLARK, David, Scott ,  BREEZE-STRINGFELLOW, Andrew

    Inventor： BEACHER, Brent, Franklin ,  CLARK, David, Scott ,  BREEZE-STRINGFELLOW, Andrew

    IPC: F01D5/14

    CPC classification number: F04D29/324 ,  F01D5/141 ,  Y02T50/673

    Abstract: A rotor blade having an airfoil for a compressor is described. The airfoil has an airfoil root, an airfoil tip located at a spanwise distance from the airfoil root, a leading edge extending from the airfoil root to the airfoil tip, an inner span region ("S 1 ") between the airfoil root and a first height location on the airfoil leading edge, a midspan region ("S2") between the first height location and a second height location on the airfoil leading edge located radially outward from the first height location; an outer span region ("S3") between the second height location and the airfoil tip, wherein the airfoil has a normalized camber profile such that the normalized camber increases in the outer span region in a spanwise direction towards the tip and is more than 2.2 in the outer span region.

    Abstract translation: 描述了具有用于压缩机的翼型的转子叶片。 翼型件具有翼型根部，翼型端部位于与翼型根部的翼展方向距离处，从翼型根部延伸到翼型端部的前缘，在翼型根部和第一翼型件之间的内部跨距区域（“S1”） 在翼型前缘上的高度位置，位于第一高度位置与位于第一高度位置径向向外的翼型前缘上的第二高度位置之间的中跨区域（“S2”）; 在第二高度位置和翼型尖端之间的外跨距区域（“S3”），其中翼型件具有归一化的弧形轮廓，使得归一化的外倾角在翼跨方向上朝向顶端的外跨距区域增加，并且大于2.2 在外跨区域。

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