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1. 发明申请

WO2014143413A3 SEAL ASSEMBLY IN A GAS TURBINE ENGINE INCLUDING GROOVES IN A RADIALLY OUTWARDLY FACING SIDE OF A PLATFORM AND IN A INWARDLY FACING SIDE OF AN INNER SHROUD 审中-公开
标题翻译：密封组件在气体涡轮发动机中，其中包括平台内的一个平坦的外部平台和内部的一个正面的侧面
公开(公告)号：WO2014143413A3
公开(公告)日：2014-12-18
申请号：PCT/US2014012525
申请日：2014-01-22
申请人： SIEMENS AG , LEE CHING-PANG
发明人： LEE CHING-PANG
IPC分类号： F01D11/00 , F01D5/08 , F01D11/04
CPC分类号： F01D11/001 , F01D11/02 , F05D2240/80 , F05D2250/37 , F05D2250/38 , F05D2250/71 , F05D2260/14
摘要： A seal assembly (50) between a disc cavity and a turbine section (26) hot gas path includes a stationary vane assembly (12) with an inner shroud (16) and a rotating blade assembly (18) downstream from the vane assembly and including a plurality of blades that are supported on a platform (28) and rotate with a turbine rotor and the platform during operation of the engine. The inner shroud (16) comprises a radially innwardly facing suface (46) comprising vane grooves (60), and the platform includes a radially and axially facing surface (146), and a plurality of grooves (160) extending into the said surface. The grooves (60, 160) are arranged such that a space is defined between adjacent grooves. During operation of the engine, the grooves guide purge air out of the disc cavity toward the hot gas path such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path.
摘要翻译：在盘腔和涡轮部分（26）热气路径之间的密封组件（50）包括具有内护罩（16）和在叶片组件下游的旋转叶片组件（18）的静止叶片组件（12），并且包括多个叶片，其被支撑在平台（28）上并在发动机运行期间与涡轮转子和平台一起旋转。内护罩（16）包括径向向内面向的包括叶片槽（60）的表面（46），并且所述平台包括径向和轴向面对的表面（146）以及延伸到所述表面中的多个凹槽（160）。凹槽（60,160）被布置成使得在相邻凹槽之间形成空间。在发动机操作期间，凹槽将吹扫空气从盘腔朝向热气路径引导，使得净化空气相对于热气流通过热气路径的方向在所需方向上流动。

2. 发明申请

WO2014113162A3 TURBINE BLADE WITH INTEGRATED SERPENTINE AND AXIAL TIP COOLING CIRCUITS 审中-公开
标题翻译：具有集成SERPENTINE和轴向冷却电路的涡轮叶片
公开(公告)号：WO2014113162A3
公开(公告)日：2014-12-11
申请号：PCT/US2013075034
申请日：2013-12-13
申请人： SIEMENS AG , LEE CHING-PANG
发明人： LEE CHING-PANG
IPC分类号： F01D5/18 , F01D5/20
CPC分类号： F01D5/187 , F01D5/186 , F01D5/20 , F05D2240/307 , F05D2250/185 , F05D2250/75 , F05D2260/201 , F05D2260/202 , F05D2260/2212 , F05D2260/2214
摘要： An air cooled turbine blade (10) including leading and trailing edges (22, 24), and pressure and suction side walls (18, 20) extending between the leading and trailing edges. Leading and trailing edge cooling circuits (34, 36) extend spanwise adjacent to the leading and trailing edges, respectively. A forward flow mid-section serpentine cooling circuit (38) extends spanwise and is located between the leading and trailing edge cooling circuits. An axial tip cooling circuit (40) extends in the chordal direction and is located between a tip cap of the blade and the serpentine cooling circuit at an outer end of the serpentine cooling circuit. The axial tip cooling circuit has a forward end (41) receiving cooling air from a final channel (62) of the serpentine cooling circuit and discharges the cooling air adjacent to the trailing edge. A method for cooling a corresponding turbine blade (10).
摘要翻译：包括前缘和后缘（22,24）的空气冷却涡轮机叶片（10）以及在前缘和后缘之间延伸的压力和吸力侧壁（18,20）。前缘和后缘冷却回路（34,36）分别沿着前缘和后缘分别延伸。向前流动的中段蛇形冷却回路（38）沿翼展方向延伸并且位于前缘和后缘冷却回路之间。轴向末端冷却回路（40）在弦线方向上延伸，位于蛇形冷却回路的外端处，位于叶片的顶盖和蛇形冷却回路之间。轴向末端冷却回路具有从蛇形冷却回路的最终通道（62）接收冷却空气的前端（41）并排出与后缘相邻的冷却空气。一种用于冷却相应的涡轮叶片（10）的方法。

3. 发明申请

WO2011050025A2 AIRFOIL INCORPORATING TAPERED COOLING STRUCTURES DEFINING COOLING PASSAGEWAYS 审中-公开
标题翻译：定义冷却通道的飞轮冷却结构
公开(公告)号：WO2011050025A2
公开(公告)日：2011-04-28
申请号：PCT/US2010053317
申请日：2010-10-20
申请人： SIEMENS ENERGY INC , LEE CHING-PANG , MARRA JOHN J , MIKRO SYSTEMS INC
发明人： LEE CHING-PANG , MARRA JOHN J
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , B22C9/103 , F05D2230/21 , F05D2240/122 , F05D2240/304 , F05D2250/18 , F05D2250/292
摘要： A gas turbine engine (10) and an airfoil (50) for use therein, the airfoil (50) having a structure (128) containing cooling passageways (110, 120) extending between a chamber (100) and a series of apertures (78) positioned along the trailing edge (72) through which cooling fluid (144) received from the chamber (100) exits the airfoil (50), wherein the structure (128) is characterized by a variable thickness (t) between the pressure and suction sidewalls (74, 76) of the airfoil as a function of position along the cooling passageways (110, 120) such that each in a plurality of cooling passageways are characterized by a cross sectional flow area (170, 174) which decreases as a function of distance from the chamber (100).
摘要翻译：一种用于其中的燃气涡轮发动机（10）和翼型件（50），所述翼型件（50）具有包括在室（100）和一系列孔（78）之间延伸的冷却通道（110,120）的结构（128）），其沿着所述后缘（72）定位，从所述腔室（100）接收的冷却流体（144）通过所述后缘离开所述翼型件），其中所述结构（128）的特征在于所述压力和吸力作为沿着冷却通道（110,120）的位置的函数的翼型件的侧壁（74,76），使得在多个冷却通道中的每一个的特征在于作为功能减小的横截面流动面积（170,174）距离室（100）的距离。

4. 发明申请

WO2012039926A2 COOLED COMPONENT WALL IN A TURBINE ENGINE 审中-公开
标题翻译：涡轮发动机冷却组件墙
公开(公告)号：WO2012039926A2
公开(公告)日：2012-03-29
申请号：PCT/US2011050594
申请日：2011-09-07
申请人： SIEMENS ENERGY INC , ZUNIGA HUMBERTO A , LEE CHING-PANG , CRAWFORD MICHAEL E
发明人： ZUNIGA HUMBERTO A , LEE CHING-PANG , CRAWFORD MICHAEL E
IPC分类号： F03B11/00 , B21D53/02
CPC分类号： F01D5/186 , F05D2230/90 , F05D2250/13 , F05D2250/324 , Y10T29/4935
摘要： A component wall in a turbine engine includes a substrate, a diffusion section, and at least one cooling passage. The diffusion section is located in a surface of the substrate and is defined by a first sidewall and a second sidewall. The cooling passage(s) include an outlet portion through which cooling air exits in a direction toward the first sidewall. The outlet portion includes a rear section, a front section, and an inner wall having proximal and distal ends. The rear section is located between the first and second sidewalls. The front section extends between the first sidewall and the distal end of the inner wall. The first sidewall extends into the outlet portion of the cooling passage(s) to the inner wall and extends from the first lateral wall to the second lateral wall so as to block the front section of the outlet portion.
摘要翻译：涡轮发动机中的部件壁包括基板，扩散部分和至少一个冷却通道。扩散部分位于衬底的表面中并且由第一侧壁和第二侧壁限定。冷却通道包括出口部分，冷却空气通过该出口部分朝向第一侧壁的方向流出。出口部分包括后部，前部和具有近端和远端的内壁。后部位于第一和第二侧壁之间。前部分在第一侧壁和内壁的远端之间延伸。第一侧壁延伸到冷却通道的出口部分到内壁，并从第一侧壁延伸到第二侧壁，以阻挡出口部分的前部。

5. 发明申请

WO2010051110A2 CRENELATED TURBINE NOZZLE 审中-公开
标题翻译： CRENELATED涡轮喷嘴
公开(公告)号：WO2010051110A2
公开(公告)日：2010-05-06
申请号：PCT/US2009057374
申请日：2009-09-18
申请人： GEN ELECTRIC , SCOGGINS PATRICK JARVIS , LAFLEN JAMES HARVEY , LEE CHING-PANG , FROST WILSON
发明人： SCOGGINS PATRICK JARVIS , LAFLEN JAMES HARVEY , LEE CHING-PANG , FROST WILSON
IPC分类号： F01D9/04 , F01D25/24
CPC分类号： F01D9/041 , F01D25/246 , F05D2220/3212 , F05D2240/55 , F05D2250/182 , Y02T50/671
摘要： A turbine nozzle (24) includes a row of vanes (38) extending radially between annular outer and inner bands (34,36). The outer band (34) includes a pair of radial flanges (46-52) defining an annular seal groove (54,56) therebetween. One of the flanges (46-52) is crenelated to improve nozzle life.
摘要翻译：涡轮喷嘴（24）包括在环形外带和内带（34,36）之间径向延伸的一排叶片（38）。外带（34）包括在其间限定环形密封槽（54,56）的一对径向凸缘（46-52）。其中一个法兰（46-52）被锯切以改善喷嘴寿命。

6. 发明申请

WO2012021194A3 COMPONENT WALL HAVING DIFFUSION SECTIONS FOR COOLING IN A TURBINE ENGINE 审中-公开
标题翻译：具有用于在涡轮发动机中冷却的扩散部分的部件壁
公开(公告)号：WO2012021194A3
公开(公告)日：2012-04-05
申请号：PCT/US2011037084
申请日：2011-05-19
申请人： SIEMENS ENERGY INC , LEE CHING-PANG , UM JAE Y , MUNSHI MRINAL , ZUNIGA HUMBERTO A
发明人： LEE CHING-PANG , UM JAE Y , MUNSHI MRINAL , ZUNIGA HUMBERTO A
IPC分类号： F01D5/18 , F01D25/12
CPC分类号： F01D25/12 , F01D5/18 , F01D5/186 , Y10T29/4932
摘要： A film cooling structure formed in a component wall of a turbine engine and a method of making the film cooling structure. The film cooling structure includes a plurality of individual diffusion sections ( 20 ) formed in the wall, each diffusions section including a single cooling passage ( 42 ) for directing cooling air toward a protuberance ( 30 ) of a wall defining the diffusion section. The film cooling structure may be formed with a masking template including apertures defining shapes of a plurality of to-be- formed diffusion sections in the wall. A masking material ( 76 ) can be applied to the wall into the apertures in the masking template so as to block outlets of cooling passages exposed through the apertures. The masking template can be removed and a material may be applied on the outer surface of the wall such that the material defines the diffusion sections once the masking material is removed.
摘要翻译：形成在涡轮发动机的部件壁上的薄膜冷却结构以及制造薄膜冷却结构的方法。薄膜冷却结构包括形成在壁中的多个单独的扩散部分（20），每个扩散部分包括用于将冷却空气引导到限定扩散部分的壁的突起（30）的单个冷却通道（42）。膜冷却结构可以由掩模模板形成，该掩模模板包括限定壁中多个待形成的扩散部分的形状的孔。可以将屏蔽材料（76）施加到屏蔽模板中的孔中，以阻止通过孔暴露的冷却通道的出口。可以去除掩模模板并且可以在壁的外表面上施加材料，使得一旦去除了掩模材料，材料就限定了扩散部分。

7. 发明申请

WO2010051110A3 TURBINE NOZZLE WITH CRENELATED OUTER SHROUD FLANGE 审中-公开
标题翻译：涡轮喷嘴与外壳外部法兰
公开(公告)号：WO2010051110A3
公开(公告)日：2010-07-22
申请号：PCT/US2009057374
申请日：2009-09-18
申请人： GEN ELECTRIC , SCOGGINS PATRICK JARVIS , LAFLEN JAMES HARVEY , LEE CHING-PANG , FROST WILSON
发明人： SCOGGINS PATRICK JARVIS , LAFLEN JAMES HARVEY , LEE CHING-PANG , FROST WILSON
IPC分类号： F01D9/04 , F01D25/24
CPC分类号： F01D9/041 , F01D25/246 , F05D2220/3212 , F05D2240/55 , F05D2250/182 , Y02T50/671
摘要： A turbine nozzle (24) includes a row of vanes (38) extending radially between annular outer and inner bands (34,36). The outer band (34) includes a pair of radial flanges (46-52) defining an annular seal groove (54,56) therebetween. One of the flanges (46-52) is crenelated to improve nozzle life.
摘要翻译：涡轮喷嘴（24）包括在环形外带和内带（34,36）之间径向延伸的一排叶片（38）。外带（34）包括在其间限定环形密封槽（54,56）的一对径向凸缘（46-52）。其中一个法兰（46-52）被锯切以改善喷嘴寿命。

8. 发明申请

WO2010068391A2 BANKED PLATFORM TURBINE BLADE 审中-公开
标题翻译： BANKED平台涡轮叶片
公开(公告)号：WO2010068391A2
公开(公告)日：2010-06-17
申请号：PCT/US2009065361
申请日：2009-11-20
申请人： GEN ELECTRIC , PANDEY VIDHU SHEKHAR , CLEMENTS JEFFREY DONALD , LEE CHING-PANG
发明人： PANDEY VIDHU SHEKHAR , CLEMENTS JEFFREY DONALD , LEE CHING-PANG
IPC分类号： F01D5/14
CPC分类号： F01D5/145 , F01D5/143 , Y02T50/673
摘要： A turbine blade includes an airfoil and integral platform at the root thereof. The platform is contoured in elevation from a bank adjacent the pressure side of the airfoil to a trough commencing behind the airfoil leading edge.
摘要翻译：涡轮机叶片包括在其根部处的翼型件和整体式平台。平台的高度是从靠近翼型的压力侧的一个堤岸到从翼型前缘的后面开始的槽。

9. 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。

10. 发明申请

WO2015116325A3 TURBINE AIRFOIL COOLING SYSTEM WITH NONLINEAR TRAILING EDGE EXIT SLOTS 审中-公开
标题翻译：涡轮机空气冷却系统与非线性拖车边缘出口滑雪
公开(公告)号：WO2015116325A3
公开(公告)日：2015-10-29
申请号：PCT/US2014070714
申请日：2014-12-17
申请人： SIEMENS AG , SIEMENS ENERGY INC
发明人： LEE CHING-PANG
IPC分类号： F01D5/18 , B22C7/02 , B22C9/04 , B22C9/10
CPC分类号： F01D5/186 , B22C7/02 , B22C9/04 , B22C9/043 , B22C9/10 , F01D5/187 , F05D2240/122 , F05D2240/304 , F05D2250/183 , F05D2250/184
摘要： A cooling system for a turbine airfoil of a turbine engine having a trailing edge cooling channel formed from a central trailing edge cooling channel and at least one trailing edge exit slot with a nonlinear longitudinal axis is disclosed. The trailing edge exit slot may be defined by ribs (24) having wavy side edges that form a jagged edge. As such, the nonlinear longitudinal axis (22) of the trailing edge exit slot reduces the effective flow area, generates impingement and turbulence to increase heat transfer and provides sufficient mechanical strength for better casting yield without overflowing for better performance. The nonlinear trailing edge exit slot may be formed using a ceramic core (106) and investment casting.
摘要翻译：公开了一种用于涡轮发动机的涡轮叶片的冷却系统，其具有由中央后缘冷却通道形成的后缘冷却通道和至少一个具有非线性纵向轴线的后缘出口槽。后缘出口槽可以由具有形成锯齿状边缘的波状侧边缘的肋（24）限定。因此，后缘出口槽的非线性纵向轴线（22）减小有效流动面积，产生冲击和湍流以增加热传递，并提供足够的机械强度以获得更好的铸造产量而不会溢出以获得更好的性能。非线性后缘出口槽可以使用陶瓷芯（106）和熔模铸造形成。

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