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71. 发明申请

US20120057960A1 RING SEGMENT WITH FORKED COOLING PASSAGES 有权
标题翻译：带有冷却通道的环形分段
公开(公告)号：US20120057960A1
公开(公告)日：2012-03-08
申请号：US13213459
申请日：2011-08-19
申请人： Eric C. Berrong , Ching-Pang Lee , Akash Bhatia , Ryan S. Yamane , Stefan Tschirren , Leonard J. Meyer
发明人： Eric C. Berrong , Ching-Pang Lee , Akash Bhatia , Ryan S. Yamane , Stefan Tschirren , Leonard J. Meyer
IPC分类号： F01D9/02
CPC分类号： F01D11/08 , F05D2250/70 , F05D2260/20
摘要： A ring segment is provided for a gas turbine engine includes a panel and a cooling system. Cooling fluid is provided to an outer side of the panel and an inner side of the panel defines at least a portion of a hot gas flow path through the engine. The cooling system is located within that panel and receives cooling fluid from the outer side of the panel for cooling the panel. The cooling system includes a plurality of cooling fluid passages that receive cooling fluid from the outer side of the panel. The cooling fluid passages each have a generally axially extending portion that includes at least one fork. The fork(s) divide each cooling fluid passage into at least two downstream portions that each receives cooling fluid from the respective axially extending portion.
摘要翻译：提供了一种用于燃气涡轮发动机的环段，其包括面板和冷却系统。冷却流体设置在面板的外侧，并且面板的内侧限定通过发动机的热气体流路的至少一部分。冷却系统位于该面板内并从面板的外侧接收冷却流体以冷却面板。冷却系统包括从板的外侧接收冷却流体的多个冷却流体通道。冷却流体通道各自具有包括至少一个叉的大致轴向延伸的部分。叉子将每个冷却流体通道分成至少两个下游部分，每个下游部分从相应的轴向延伸部分接收冷却流体。

72. 发明申请

US20120014808A1 NEAR-WALL SERPENTINE COOLED TURBINE AIRFOIL 有权
标题翻译：近壁式冷却涡轮机
公开(公告)号：US20120014808A1
公开(公告)日：2012-01-19
申请号：US12836060
申请日：2010-07-14
申请人： Ching-Pang Lee
发明人： Ching-Pang Lee
IPC分类号： F01D5/18
CPC分类号： F01D25/12 , F01D5/187 , F05D2250/185 , F05D2260/202 , F05D2260/22141
摘要： A serpentine coolant flow path (54A-54G) formed by inner walls (50, 52) in a cavity (49) between pressure and suction side walls (22, 24) of a turbine airfoil (20A). A coolant flow (58) enters (56) an end of the airfoil, flows into a span-wise channel (54A), then flows forward (54B) over the inner surface of the pressure side wall, then turns behind the leading edge (26), and flows back along a forward part of the suction side wall, then follows a loop (54E) forward and back around an inner wall (52), then flows along an intermediate part of the suction side wall, then flows into an aft channel (54G) between the pressure and suction side walls, then exits the trailing edge (28). This provides cooling matched to the heating topography of the airfoil, minimizes differential thermal expansion, revives the coolant, and minimizes the flow volume needed.
摘要翻译：由涡轮机翼（20A）的压力侧和吸力侧壁（22,24）之间的空腔（49）中的内壁（50,52）形成的蛇形冷却剂流动路径（54A-54G）。冷却剂流（58）进入（56）翼型件的端部，流入跨度通道（54A），然后在压力侧壁的内表面上向前（54B）流动，然后在前缘 26），并且沿吸力侧壁的前部流回，然后围绕内壁（52）向前和向后循环（54E），然后沿着吸力侧壁的中间部分流动，然后流入在压力侧和吸力侧壁之间的后通道（54G），然后离开后缘（28）。这提供了与翼型件的加热形状相匹配的冷却，最小化差异热膨胀，恢复冷却剂，并最小化所需的流量。

73. 发明申请

US20110293434A1 METHOD OF CASTING A COMPONENT HAVING INTERIOR PASSAGEWAYS 有权
标题翻译：铸造具有内部通道的部件的方法
公开(公告)号：US20110293434A1
公开(公告)日：2011-12-01
申请号：US13087428
申请日：2011-04-15
申请人： Ching-Pang Lee , Gary B. Merrill , Andrew J. Burns
发明人： Ching-Pang Lee , Gary B. Merrill , Andrew J. Burns
IPC分类号： F01D5/14 , B32B15/00 , B22D25/02 , B32B3/10 , B22C9/02 , B22C9/10
CPC分类号： B22C9/043 , B22C7/02 , B22C7/026 , B22C9/04 , B22C9/22 , B22D17/00 , B22D29/00 , Y10T428/12361
摘要： A method of casting a component (42) having convoluted interior passageways (44). A desired three dimensional structure corresponding to a later-formed metal alloy component is formed by stacking a plurality of sheets (18, 20) of a fugitive material.The sheets contain void areas (22) corresponding to a desired interior passageway in the metal alloy component. A ceramic slurry material is cast into the three dimensional structure to form either a ceramic core (34) or a complete ceramic casting vessel (38). If just a ceramic core is formed, a wax pattern is formed around the ceramic core and an exterior ceramic shell (38) is formed around the wax pattern by a dipping process prior to the removal of the fugitive material and wax. An alloy component having the desired interior passageway is cast into the casting vessel after the fugitive material is removed.
摘要翻译：一种铸造具有卷曲内部通道（44）的部件（42）的方法。对应于后来形成的金属合金部件的期望的三维结构通过堆叠多个片状物（18,20）而形成。这些板包含对应于金属合金部件中期望的内部通道的空隙区域（22）。将陶瓷浆料材料铸造成三维结构以形成陶瓷芯（34）或完整的陶瓷铸造容器（38）。如果仅形成陶瓷芯，则在陶瓷芯周围形成蜡图案，并且在除去逸散材料和蜡之前通过浸渍工艺在蜡图案周围形成外部陶瓷壳（38）。具有所需内部通道的合金部件在除去逸散材料之后被浇注入铸造容器中。

74. 发明授权

US07870719B2 Plasma enhanced rapidly expanded gas turbine engine transition duct 有权
标题翻译：等离子体增强了快速扩大的燃气轮机发动机过渡管道
公开(公告)号：US07870719B2
公开(公告)日：2011-01-18
申请号：US11580788
申请日：2006-10-13
申请人： Ching-Pang Lee , Aspi Rustom Wadia , David Glenn Cherry , Scott Michael Carson
发明人： Ching-Pang Lee , Aspi Rustom Wadia , David Glenn Cherry , Scott Michael Carson
IPC分类号： F02H1/00
CPC分类号： F01D9/041 , F01D5/143 , F01D5/145 , F05D2260/221 , F05D2270/172 , Y02T50/671 , Y02T50/673 , Y02T50/675
摘要： A plasma enhanced rapidly expanded duct system includes a gas turbine engine inter-turbine transition duct having radially spaced apart conical inner and outer duct walls extending axially between a duct inlet and a duct outlet. A conical plasma generator produces a conical plasma along the outer duct wall. An exemplary embodiment of the conical plasma generator is mounted to the outer duct wall and including radially inner and outer electrodes separated by a dielectric material. The dielectric material is disposed within a conical groove in a radially inwardly facing surface of the outer duct wall. An AC power supply is connected to the electrodes to supply a high voltage AC potential to the electrodes.
摘要翻译：等离子体增强的快速扩张的管道系统包括燃气涡轮发动机涡轮机间过渡管道，其具有在管道入口和管道出口之间轴向延伸的径向间隔开的锥形内部和外部管道壁。锥形等离子体发生器沿着外管道壁产生锥形等离子体。锥形等离子体发生器的示例性实施例安装到外部管道壁并且包括由电介质材料隔开的径向内部和外部电极。介电材料设置在外管道壁的径向向内的表面内的锥形槽内。 AC电源连接到电极以向电极提供高电压AC电位。

75. 发明申请

US20100284795A1 Plasma Clearance Controlled Compressor 审中-公开
标题翻译：等离子体间隙控制压缩机
公开(公告)号：US20100284795A1
公开(公告)日：2010-11-11
申请号：US11966309
申请日：2007-12-28
申请人： Aspi Rustom Wadia , David Scott Clark , Ching-Pang Lee , Andrew Breeze-Stringfellow , Gregory Scott McNulty
发明人： Aspi Rustom Wadia , David Scott Clark , Ching-Pang Lee , Andrew Breeze-Stringfellow , Gregory Scott McNulty
IPC分类号： F01D11/08
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。

76. 发明授权

US07785067B2 Method and system to facilitate cooling turbine engines 有权
标题翻译：便于冷却涡轮发动机的方法和系统
公开(公告)号：US07785067B2
公开(公告)日：2010-08-31
申请号：US11565229
申请日：2006-11-30
申请人： Ching-Pang Lee , Eric Alan Estill , James Harvey Laflen , Paul Hadley Vitt , Michael Elliot Wymore
发明人： Ching-Pang Lee , Eric Alan Estill , James Harvey Laflen , Paul Hadley Vitt , Michael Elliot Wymore
IPC分类号： F01D25/12
CPC分类号： F01D25/12 , F01D9/04 , F01D11/08 , F01D11/24 , F01D25/246 , F05D2240/11 , F05D2240/81 , F05D2250/314 , Y02T50/671 , Y02T50/676 , Y10T29/49236
摘要： A method of assembling a gas turbine engine is provided. The method includes coupling at least one turbine nozzle segment within the gas turbine engine. The at least one turbine nozzle segment includes at least one airfoil vane extending between an inner band and an outer band that includes an aft flange and a radial inner surface. The method also includes coupling at least one turbine shroud segment downstream from the at least one turbine nozzle segment, wherein the at least one turbine shroud segment includes a leading edge and a radial inner surface, and coupling a cooling fluid source in flow communication with the at least one turbine nozzle segment such that cooling fluid channeled to each turbine nozzle outer band aft flange is directed at an oblique discharge angle towards the leading edge of the at least one turbine shroud segment.
摘要翻译：提供一种组装燃气涡轮发动机的方法。该方法包括联接燃气涡轮发动机内的至少一个涡轮喷嘴段。至少一个涡轮喷嘴段包括在内带和外带之间延伸的至少一个翼型叶片，其包括后翼缘和径向内表面。该方法还包括将至少一个涡轮机护罩段联接到至少一个涡轮喷嘴段的下游，其中至少一个涡轮机护罩段包括前缘和径向内表面，并且将冷却流体源与至少一个涡轮喷嘴段，使得被引导到每个涡轮喷嘴外带后缘的冷却流体朝向至少一个涡轮机护罩段的前缘以倾斜的排出角度引导。

77. 发明授权

US07740444B2 Methods and system for cooling integral turbine shround assemblies 有权
标题翻译：冷却整体涡轮机组件的方法和系统
公开(公告)号：US07740444B2
公开(公告)日：2010-06-22
申请号：US11565387
申请日：2006-11-30
申请人： Ching-Pang Lee , James Harvey Laflen , Dustin Alfred Placke , George Elliott Moore , Katherine Jaynetorrence Andersen , Daniel Verner Jones
发明人： Ching-Pang Lee , James Harvey Laflen , Dustin Alfred Placke , George Elliott Moore , Katherine Jaynetorrence Andersen , Daniel Verner Jones
IPC分类号： F01D25/12
CPC分类号： F01D11/24 , F01D25/246 , F05D2260/201 , F05D2260/205 , Y02T50/671 , Y02T50/676
摘要： A method for cooling a turbine shroud assembly includes providing a turbine shroud assembly including a shroud segment having a leading edge, a trailing edge and a midsection defined therebetween. A shroud support circumferentially spans and supports the shroud segment. The shroud support includes a forward hanger coupled to the leading edge, a midsection hanger coupled to the midsection and an aft hanger coupled to the trailing edge. An annular shroud ring structure includes a midsection position control ring coupled to the midsection hanger and an aft position control ring coupled to the aft hanger. Cooling air is extracted from a compressor positioned upstream of the turbine shroud assembly. Cooling air is metered through the shroud support directly into only at least one active convection cooling zone defined between the shroud segment and the shroud support while substantially preventing cooling air from entering an inactive convection cooling zone positioned radially outwardly from the at least one active convection cooling zone and defined between the shroud support and the shroud ring structure and between the midsection position control ring and the aft position control ring.
摘要翻译：一种用于冷却涡轮机护罩组件的方法包括提供一种涡轮机护罩组件，其包括具有前缘，后缘和在其间限定的中部的护罩段。护罩支撑件周向地跨越并支撑护罩段。护罩支撑件包括联接到前缘的前悬挂器，联接到中部的中间吊架和耦合到后缘的后挂架。环形护罩环结构包括连接到中间悬挂架的中央位置控制环和联接到后悬挂架的后部位置控制环。从位于涡轮机罩组件上游的压缩机抽出冷却空气。冷却空气通过护罩支撑件计量直接仅限于限定在护罩区段和护罩支撑件之间的至少一个主动对流冷却区域，同时基本上防止冷却空气进入从至少一个主动对流冷却器径向向外定位的非活动对流冷却区域并且限定在护罩支撑件和护罩环结构之间以及中间位置控制环和后部位置控制环之间。

78. 发明申请

US20100143139A1 BANKED PLATFORM TURBINE BLADE 有权
标题翻译： BANKED平台涡轮叶片
公开(公告)号：US20100143139A1
公开(公告)日：2010-06-10
申请号：US12330783
申请日：2008-12-09
申请人： Vidhu Shekhar Pandey , Jeffrey Donald Clements , Ching-Pang Lee
发明人： Vidhu Shekhar Pandey , Jeffrey Donald Clements , Ching-Pang Lee
IPC分类号： F01D5/22 , 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。

79. 发明申请

US20090324422A1 Cascade tip baffle airfoil 有权
标题翻译：级联顶端挡板翼型
公开(公告)号：US20090324422A1
公开(公告)日：2009-12-31
申请号：US11507120
申请日：2006-08-21
申请人： Kevin Samuel Klasing , Ching-Pang Lee , Paul Hadley Vitt , Brian David Keith
发明人： Kevin Samuel Klasing , Ching-Pang Lee , Paul Hadley Vitt , Brian David Keith
IPC分类号： F01D5/18
CPC分类号： F01D5/20 , F01D5/187 , F05D2250/70 , F05D2260/202 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A turbine blade includes an airfoil tip with first and second ribs extending along the opposite pressure and suction sides. The ribs extend outwardly from a tip floor and are joined together at opposite leading and trailing edges. A cascade tip baffle transversely bridges the two ribs above the tip floor forward of the maximum width of the tip to partition the tip chordally into corresponding tip pockets on opposite sides of the baffle.
摘要翻译：涡轮叶片包括具有沿相对的压力和吸力侧延伸的第一和第二肋的翼型端。肋从尖端底部向外延伸并且在相对的前缘和后缘处连接在一起。级联顶端挡板将尖端底部上方的两个肋横向地桥接在尖端的最大宽度的前方，以将端部弦状地分隔成挡板相对侧上的相应的尖端口。

80. 发明授权

US07591070B2 Turbine blade tip squealer and rebuild method 失效
标题翻译：涡轮叶尖尖叫声和重建方法
公开(公告)号：US07591070B2
公开(公告)日：2009-09-22
申请号：US11766488
申请日：2007-06-21
申请人： Ching-Pang Lee
发明人： Ching-Pang Lee
IPC分类号： B23P15/02 , F01D5/20
CPC分类号： B23P6/007 , F01D5/005 , F01D5/20 , F05D2260/202 , Y10T29/49318 , Y10T29/49337 , Y10T29/49339 , Y10T29/49341 , Y10T29/49728 , Y10T29/53091
摘要： A turbine blade with a tip squealer and method of rebuilding a turbine blade for a gas turbine engine. The blade is of the type including an airfoil having first and second spaced-apart sidewalls defining an interior void and joined at a leading edge and a trailing edge. The first and second sidewalls extending from a root disposed adjacent the dovetail to a tip cap for channeling combustion gases, and a squealer tip including at least one tip rib extending outwardly from the tip cap. The method includes the steps of removing the squealer tip, including the at least one rib tip, from the tip cap and adding new material to the tip cap to serve as a new squealer tip. A plurality of spaced-apart notches is formed in the new material between the leading edge and the trailing edge of the airfoil. At least one hole is formed in each notch communicating with the interior void of the airfoil for channeling cooling air from the interior void of the airfoil to thereby form a squealer tip.
摘要翻译：具有尖端喷嘴的涡轮机叶片和用于重建用于燃气涡轮发动机的涡轮机叶片的方法。叶片类型包括具有限定内部空隙并且在前缘和后缘处连接的第一和第二间隔开的侧壁的翼型件。所述第一和第二侧壁从邻近所述燕尾榫设置的根部延伸到用于引导燃烧气体的尖端帽，以及尖叫尖端，其包括从所述尖端帽向外延伸的至少一个尖端肋。该方法包括以下步骤：从顶盖移除包括至少一个肋尖端的尖叫尖端，并将新材料添加到尖端盖以用作新的尖叫尖端。在翼缘的前缘和后缘之间的新材料中形成多个间隔开的凹口。在与翼型件的内部空隙连通的每个凹口中形成至少一个孔，用于从翼型的内部空间引导冷却空气，从而形成尖叫尖端。

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