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1. 发明申请

WO2009085467A1 COMPRESSOR BLADE TIP CLEARANCE CONTROL SYSTEM WITH A PLASMA ACTUATOR, COMPRESSOR AND GAS TURBINE ENGINE WITH SUCH A CONTROL SYSTEM 审中-公开
标题翻译：压缩机叶片间隙控制系统，具有等离子体致动器，压缩机和具有这种控制系统的气体涡轮发动机
公开(公告)号：WO2009085467A1
公开(公告)日：2009-07-09
申请号：PCT/US2008084315
申请日：2008-11-21
申请人： GEN ELECTRIC , WADIA ASPI RUSTOM , CLARK DAVID SCOTT , LEE CHING-PANG , BREEZE-STRINGFELLOW ANDREW , MCNULTY GROGORY SCOTT
发明人： WADIA ASPI RUSTOM , CLARK DAVID SCOTT , LEE CHING-PANG , BREEZE-STRINGFELLOW ANDREW , MCNULTY GROGORY SCOTT
IPC分类号： F01D11/20 , F04D29/16
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。

2. 发明申请

WO2012134833A3 HIGH CAMBER COMPRESSOR ROTOR BLADE 审中-公开
标题翻译：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
申请人： GEN ELECTRIC , BEACHER BRENT FRANKLIN , CLARK DAVID SCOTT , BREEZE-STRINGFELLOW ANDREW
发明人： BEACHER BRENT FRANKLIN , CLARK DAVID SCOTT , BREEZE-STRINGFELLOW ANDREW
IPC分类号： F04D29/32 , F01D5/14
CPC分类号： F04D29/324 , F01D5/141 , Y02T50/673
摘要： 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.
摘要翻译：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。

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