公开(公告)号：EP2230460A3

公开(公告)日：2014-12-31

申请号：EP10156639.6

申请日：2010-03-16

申请人： General Electric Company

发明人： WIEDENHOEFER, James Fredric ,  RASHEED, Adam

IPC分类号： F23R7/00

CPC分类号： F23R7/00 ,  F23R2900/00013

摘要： An engine (100) contains a compressor stage (101), a plurality of pulse detonation combustors (103) and a rotary inlet valve structure (105) having a plurality of inlet ports through which at least air flows to enter the pulse detonation combustors during operation of the engine. Downstream of the pulse detonation combustors is a turbine stage (111). Further, the ratio of the pulse detonation combustors to the inlet ports is a non-integer.

公开(公告)号：EP2230460A2

公开(公告)日：2010-09-22

申请号：EP10156639.6

申请日：2010-03-16

申请人： General Electric Company

发明人： WIEDENHOEFER, James Fredric ,  RASHEED, Adam

IPC分类号： F23R7/00

CPC分类号： F23R7/00 ,  F23R2900/00013

摘要： An engine (100) contains a compressor stage (101), a plurality of pulse detonation combustors (103) and a rotary inlet valve structure (105) having a plurality of inlet ports through which at least air flows to enter the pulse detonation combustors during operation of the engine. Downstream of the pulse detonation combustors is a turbine stage (111). Further, the ratio of the pulse detonation combustors to the inlet ports is a non-integer.

摘要翻译： 发动机（100）包括压缩机级（101），多个脉冲爆震燃烧器（103）和具有多个入口的旋转入口阀结构（105），所述多个入口端口至少在空气中流动以进入脉冲爆震燃烧器 发动机的运行。 脉冲爆震燃烧器的下游是涡轮级（111）。 此外，脉冲爆震燃烧器与入口端口的比率是非整数。

公开(公告)号：EP3315719B1

公开(公告)日：2019-06-05

申请号：EP17196197.2

申请日：2017-10-12

申请人： General Electric Company

发明人： SNIDER, Zachary John ,  FOSTER, Gregory Thomas ,  WEBER, Joseph Antony ,  WIEDENHOEFER, James Fredric

IPC分类号： F01D5/14 ,  F01D5/18 ,  F01D9/04 ,  F01D9/06 ,  F01D25/08

公开(公告)号：EP3315719A1

公开(公告)日：2018-05-02

申请号：EP17196197.2

申请日：2017-10-12

申请人： General Electric Company

发明人： SNIDER, Zachary John ,  FOSTER, Gregory Thomas ,  WEBER, Joseph Antony ,  WIEDENHOEFER, James Fredric

IPC分类号： F01D5/14 ,  F01D5/18 ,  F01D9/04 ,  F01D9/06

CPC分类号： F01D9/065 ,  F01D5/147 ,  F01D5/186 ,  F01D5/187 ,  F01D9/041 ,  F01D9/06 ,  F01D25/08 ,  F05D2220/32 ,  F05D2240/122 ,  F05D2240/123 ,  F05D2240/124 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2260/202 ,  F05D2260/204

摘要： A turbine 216 airfoil 106 for a rotating blade 2 or stationary nozzle 2 vane includes an airfoil body 140 including a leading edge 14 and a trailing edge 116. A coolant supply passage 142 extends within the airfoil body 140, and a coolant return passage 144 extends within the airfoil body 140. A first trench 246 is in an external surface 148, 248 of the airfoil body 140, the first trench 246 extending to the trailing edge 116 and being in fluid communication with the coolant supply passage 142. A second trench 146, 152, 246, 252 is in the external surface 148, 248 of the airfoil body 140, the second trench 146, 152, 246, 252 extending to the trailing edge 116 and being in fluid communication with the coolant return passage 144 and the first trench 246. A cover 130 seats 160 in the airfoil body 140 and encloses the trenches 146, 246 to form coolant passages 18, 20, 22, 24 with the airfoil body 140. In embodiments, two coolant passages 18, 20, 22, 24 to and back from the trailing edge 116 may be used to allow for a recycling flow.

摘要翻译： 用于旋转叶片2或静止喷嘴叶片的涡轮机216翼型件106包括翼型体140，该翼型体包括前缘14和后缘116.冷却剂供应通道142在翼型体140内延伸，并且冷却剂返回通道144延伸 在翼型体140内。第一沟槽246位于翼型体140的外表面148,248中，第一沟槽246延伸到后缘116并且与冷却剂供应通道142流体连通。第二沟槽146 ，152,246,252位于翼型体140的外表面148,248中，第二沟槽146,152,246,252延伸到后缘116并且与冷却剂返回通道144流体连通，并且第一沟槽 沟槽246.盖130在翼型体140中放置160并封闭沟槽146,246以与翼型体140形成冷却剂通道18,20,22,24。在实施例中，两个冷却剂通道18,20,22,24 往返于后缘11 6可以用于允许回收流动。