公开(公告)号：US20060288686A1

公开(公告)日：2006-12-28

申请号：US11145848

申请日：2005-06-06

申请人： David Cherry ,  Robert Beacock ,  William Clifford ,  Robert Orlando ,  Thomas Moniz ,  Ching-Pang Lee

发明人： David Cherry ,  Robert Beacock ,  William Clifford ,  Robert Orlando ,  Thomas Moniz ,  Ching-Pang Lee

IPC分类号： F02K3/04 ,  F02C3/10

CPC分类号： F02C3/067 ,  F01D5/142 ,  F01D9/02 ,  F01D9/041 ,  F01D9/065 ,  F02K3/072 ,  F05D2240/127 ,  Y02T50/671 ,  Y02T50/673

摘要： A turbofan engine includes a fan, compressor, combustor, high pressure turbine, and low pressure turbine joined in serial flow communication. The high pressure turbine includes two stages of rotor blades to effect corresponding exit swirl in the combustion gases discharged therefrom. A transition duct includes fairings extending between platforms for channeling the combustion gases to the low pressure turbine with corresponding swirl. First stage rotor blades in the low pressure turbine are oriented oppositely to the rotor blades in the high pressure turbine for counterrotation.

公开(公告)号：US20060272314A1

公开(公告)日：2006-12-07

申请号：US11145875

申请日：2005-06-06

申请人： Thomas Moniz ,  Scott Carson ,  Robert Orlando ,  Ching-Pang Lee ,  David Cherry

发明人： Thomas Moniz ,  Scott Carson ,  Robert Orlando ,  Ching-Pang Lee ,  David Cherry

IPC分类号： F02K3/04

CPC分类号： F01D5/14 ,  F01D5/141 ,  F02C3/067 ,  F02K3/072 ,  Y02T50/671 ,  Y02T50/673

摘要： A turbofan engine includes a fan, compressor, combustor, single-stage high pressure turbine, and low pressure turbine joined in serial flow communication. First stage rotor blades in the low pressure turbine are oriented oppositely to the rotor blades in the high pressure turbine for counterrotation. First stage stator vanes in the low pressure turbine have camber and twist for carrying swirl directly between the rotor blades of the high and low pressure turbines.

公开(公告)号：US20060275111A1

公开(公告)日：2006-12-07

申请号：US11145837

申请日：2005-06-06

申请人： Robert Orlando ,  Thomas Moniz ,  Ching-Pang Lee ,  David Cherry ,  Robert Beacock ,  William Clifford ,  Scott Carson

发明人： Robert Orlando ,  Thomas Moniz ,  Ching-Pang Lee ,  David Cherry ,  Robert Beacock ,  William Clifford ,  Scott Carson

IPC分类号： F01D9/00

CPC分类号： F01D5/141 ,  F01D5/142 ,  F01D9/041 ,  F02C3/067 ,  F02K3/072 ,  F05D2220/323 ,  F05D2250/314 ,  Y02T50/671 ,  Y02T50/673

摘要： A turbine nozzle includes a row of vanes joined to radially outwardly inclined outer and inner bands. Each vane has camber and an acute twist angle for importing swirl in combustion gases discharged at trailing edges thereof. The trailing edges are tilted forwardly from the inner band to the outer band for increasing aerodynamic efficiency.

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。