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1. 发明申请

WO2015157780A1 INTERNAL COOLING SYSTEM WITH INSERT FORMING NEARWALL COOLING CHANNELS IN AN AFT COOLING CAVITY OF A GAS TURBINE AIRFOIL INCLUDING HEAT DISSIPATING RIBS 审中-公开
标题翻译：内部冷却系统，具有在气体涡轮机的空气冷却空气中形成近壁冷却通道的内部冷却系统，其中包括热排出的RIBS
公开(公告)号：WO2015157780A1
公开(公告)日：2015-10-15
申请号：PCT/US2015/026287
申请日：2015-04-17
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： LEE, Ching-Pang , UM, Jae Y. , PU, Zhengxiang , MYERS, Caleb
IPC分类号： F01D5/18 , F01D9/04
CPC分类号： F01D5/187 , F01D5/189 , F01D9/02 , F01D9/041 , F05B2250/183 , F05B2260/2241 , F05D2240/127 , F05D2260/201 , F05D2260/22141
摘要： An airfoil (10) for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more internal cavities (16) having an insert (18) contained within an aft cooling cavity (76) to form nearwall cooling channels having enhanced flow patterns is disclosed. The flow of cooling fluids in the nearwall cooling channels (20) may be controlled via a plurality of cooling fluid flow controllers (22) extending from the outer wall (12) forming the generally hollow elongated airfoil (26). In addition, heat may be extracted in the midchord region (150) via one or more heat dissipating ribs (152) extending partially between an inner surface (144) of the suction side (38) and the insert (18). In at least one embodiment, the heat dissipating ribs (152) may extend in a generally chordwise direction and be positioned from an inner diameter (92) to an outer diameter (98) of the airfoil (10) between the cooling fluid flow controllers (22) and a rib (72) separating forward and aft cooling cavities (74, 76).
摘要翻译：一种用于燃气涡轮发动机的翼型件（10），其中所述翼型件（10）包括具有一个或多个内部空腔（16）的内部冷却系统（14），所述内部空腔具有包含在后部冷却空腔（76）内的插入件（18）公开了具有增强的流动模式的形成近壁冷却通道。近壁冷却通道（20）中的冷却流体的流动可以通过从形成大致中空的细长翼型件（26）的外壁（12）延伸的多个冷却流体流量控制器（22）来控制。此外，可以通过部分地在吸入侧（38）的内表面（144）和插入件（18）之间延伸的一个或多个散热肋（152）在中间区域（150）中提取热量。在至少一个实施例中，散热肋（152）可以在大致方向的方向上延伸，并且从冷却流体流量控制器之间的翼型件（10）的内径（92）到外径（98） 22）和分离前后冷却空腔（74,76）的肋（72）。

2. 发明申请

WO2016043742A1 GAS TURBINE AIRFOIL INCLUDING INTEGRATED LEADING EDGE AND TIP COOLING FLUID PASSAGE AND CORE STRUCTURE USED FOR FORMING SUCH AN AIRFOIL 审中-公开
标题翻译：气体涡轮机空气包括集成的引导边缘和提升冷却流体通道和用于形成这种航空器的核心结构
公开(公告)号：WO2016043742A1
公开(公告)日：2016-03-24
申请号：PCT/US2014/056188
申请日：2014-09-18
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： LEE, Ching-Pang , UM, Jae Y. , HILLIER, Gerald L. , MCDONALD, Wayne J. , JOHNSON, Erik , WAYWOOD, Anthony , SCHROEDER, Eric , PU, Zhengxiang
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D9/02 , F01D25/12 , F05D2220/32 , F05D2240/303 , F05D2250/25 , F05D2260/201 , F05D2260/2212
摘要： A core structure (10) includes a first core element (16) including a leading edge section (30), a tip section (32), and a turn section (34) joining the leading edge and tip sections (30, 32). The first core element (16) is adapted to be used to form a leading edge cooling circuit (102) in a gas turbine engine airfoil (100). The leading edge cooling circuit (102) includes a cooling fluid passage (104) having a leading edge portion (106) formed by the first core element leading edge section (30), a tip portion (108) formed by the first core element tip section (32), and a turn portion (110) formed by the first core element turn section (34). Each of the leading edge portion (106), the tip portion (108), and the turn portion (110) of the cooling fluid passage (104) are formed concurrently in the airfoil (100) by the first core element (16).
摘要翻译：芯结构（10）包括：第一芯元件（16），包括前缘部分（30），尖端部分（32）和接合前缘和末端部分（30,32）的转向部分（34）。第一核心元件（16）适于用于在燃气涡轮发动机翼型件（100）中形成前缘冷却回路（102）。前缘冷却回路（102）包括：冷却流体通路（104），其具有由第一芯体前端部（30）形成的前缘部（106），由第一芯部元件末端（32）和由第一芯元件转动部分（34）形成的转弯部分（110）。通过第一芯元件（16）在翼型件（100）中同时形成冷却流体通道（104）的前缘部分（106），前端部分（108）和转弯部分（110）。

3. 发明申请

WO2013126126A3 AXIAL FLOW COMPRESSOR TIP CLEARANCE CONTROL BY AXIAL SHIFT OF ROTOR 审中-公开
公开(公告)号：WO2013126126A3
公开(公告)日：2013-08-29
申请号：PCT/US2012/068466
申请日：2012-12-07
申请人： SIEMENS ENERGY, INC. , LITTLE, David A. , PU, Zhengxiang
发明人： LITTLE, David A. , PU, Zhengxiang
IPC分类号： F01D11/22 , F04D29/16
摘要： In a turbine engine, an axial compressor is equipped with a system that moves the rotor axially in order to influence the tip clearances of cantilevered airfoils during operation. Axial movement of the rotor can reduce the tip clearances of both one cantilevered rotor blade and one cantilevered stator vane. The radially inwards flowpath boundary of the compressor is shaped in such a way that its radius increases in streamwise direction over a portion of its axial extend, at least over the 40% downstream part of its axial extend.

4. 发明申请

WO2016036367A1 INTERNAL COOLING SYSTEM WITH INSERT FORMING NEARWALL COOLING CHANNELS IN MIDCHORD COOLING CAVITIES OF A GAS TURBINE AIRFOIL 审中-公开
标题翻译：内部冷却系统，具有插入式形成气体冷却通道，在气体涡轮机空气中的冷却空气中
公开(公告)号：WO2016036367A1
公开(公告)日：2016-03-10
申请号：PCT/US2014/053978
申请日：2014-09-04
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： LEE, Ching-Pang , UM, Jae Y. , HILLIER, Gerald L. , MCDONALD, Wayne J. , ABDULLAH, Mohamed , SCHROEDER, Eric , MATTHEWS, Ralph W. , PU, Zhengxiang
IPC分类号： F01D5/18 , F01D9/04
CPC分类号： F01D9/065 , B22C9/10 , F01D5/186 , F01D5/187 , F01D5/188 , F01D5/189 , F05D2220/32 , F05D2240/122 , F05D2240/127 , F05D2250/183 , F05D2260/20 , F05D2260/201 , F05D2260/202 , F05D2260/2214
摘要： An airfoil (10) for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more internal cavities (16) having an insert (18) contained therein that forms nearwall cooling channels (20) having enhanced flow patterns is disclosed. The flow of cooling fluids in the nearwall cooling channels (20) may be controlled via a plurality of cooling fluid flow controllers (22) extending from the outer wall (24) forming the generally hollow elongated airfoil (26). The cooling fluid flow controllers (22) may be collected into spanwise extending rows (28), and the internal cooling system (14) may include one or more bypass flow reducers (30) extending from the insert (18) toward the outer wall (24) to direct the cooling fluids through the channels (20) created by the cooling fluid flow controllers (22), thereby increasing the effectiveness of the internal cooling system (14).
摘要翻译：一种用于燃气涡轮发动机的翼型件（10），其中所述翼型件（10）包括内部冷却系统（14），所述内部冷却系统（14）具有一个或多个内部空腔（16），所述内部空腔具有形成近壁冷却通道（20）的插入件（18）公开了增强的流动模式。近壁冷却通道（20）中的冷却流体的流动可以通过从形成大致中空的细长翼型件（26）的外壁（24）延伸的多个冷却流体流量控制器（22）来控制。冷却流体流量控制器（22）可以被收集到翼展方向延伸的排（28）中，并且内部冷却系统（14）可以包括从插入件（18）朝向外壁（...）延伸的一个或多个旁路减流器（30） 24）引导冷却流体通过由冷却流体流量控制器（22）产生的通道（20），从而提高内部冷却系统（14）的有效性。

5. 发明申请

WO2016036366A1 INTERNAL COOLING SYSTEM WITH INSERT FORMING NEARWALL COOLING CHANNELS IN AN AFT COOLING CAVITY OF A GAS TURBINE AIRFOIL 审中-公开
标题翻译：内部冷却系统，具有在气体涡轮机空气的冷却空气中形成近壁冷却通道
公开(公告)号：WO2016036366A1
公开(公告)日：2016-03-10
申请号：PCT/US2014/053968
申请日：2014-09-04
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： LEE, Ching-Pang , UM, Jae Y , PU, Zhengxiang , ABDULLAH, Mohamed , SCHROEDER, Eric , WAYWOOD, Anthony
IPC分类号： F01D5/18 , F01D9/04
CPC分类号： F01D5/188 , B22C9/10 , F01D5/189 , F01D9/065 , F05D2220/32 , F05D2240/122 , F05D2240/127 , F05D2250/183 , F05D2260/20 , F05D2260/201 , F05D2260/202 , F05D2260/2214
摘要： An airfoil (10) for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more internal cavities having an insert (18) contained within an aft cooling cavity (76) to form nearwall cooling channels having enhanced flow patterns is disclosed. The flow of cooling fluids in the nearwall cooling channels may be controlled via a plurality of cooling fluid flow controllers (22) extending from the outer wall (24) forming the generally hollow elongated airfoil (26). The cooling fluid flow controllers (22) may be collected into spanwise extending rows. In at least one embodiment, the cooling fluid flow controllers (22) may be positioned within a pressure side nearwall cooling channel (48) and a suction side nearwall cooling channel (50) that are both in fluid communication with a trailing edge channel (30). The trailing edge channel (30) may also include cooling fluid flow controllers (22) extending between the outer walls (12, 13) forming the pressure and suction sides.
摘要翻译：一种用于燃气涡轮发动机的翼型件（10），其中所述翼型件（10）包括具有一个或多个内部空腔的内部冷却系统（14），所述内部空腔具有包含在后部冷却腔（76）内的插入件（18），以形成近壁冷却公开了具有增强的流动模式的通道。近壁冷却通道中的冷却流体的流动可以通过从形成大致中空的细长翼型件26的外壁（24）延伸的多个冷却流体流量控制器（22）来控制。冷却流体流量控制器（22）可以被收集到横向延伸的行中。在至少一个实施例中，冷却流体流量控制器（22）可以位于与后缘通道（30）流体连通的压力侧近壁冷却通道（48）和吸入侧近壁冷却通道（50）内）。后缘通道（30）还可以包括在形成压力侧和吸力侧的外壁（12,13）之间延伸的冷却流体流量控制器（22）。

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