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71. 发明申请

US20080131261A1 METHOD AND SYSTEM TO FACILITATE ENHANCED LOCAL COOLING OF TURBINE ENGINES 有权
标题翻译：提高涡轮发动机增压局部冷却的方法和系统
公开(公告)号：US20080131261A1
公开(公告)日：2008-06-05
申请号：US11565273
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： F01D5/18 , B21D53/78 , F01D1/02
CPC分类号： F01D9/04 , F01D11/08 , F05D2240/11 , F05D2240/81 , Y02T50/671 , Y02T50/676 , Y10T29/49346 , Y10T29/53443
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, 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, and channeling the cooling fluid through at least a first group of cooling openings having a larger aggregate cross-sectional area and a second group of cooling openings having a smaller aggregate cross-sectional area to facilitate preferential cooling of the turbine shroud.
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区段联接在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，将与流体连通的冷却流体源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，并且通过至少一个第一组具有较大聚集体横截面面积的冷却开口和具有较小聚集体横截面积的第二组冷却开口，以便于涡轮机护罩的优先冷却。

72. 发明申请

US20080131259A1 METHODS AND SYSTEM FOR RECUPERATED COOLING OF INTEGRAL TURBINE NOZZLE AND SHROUD ASSEMBLIES 失效
标题翻译：整体涡轮喷嘴和风力发电机组的回收冷却方法与系统
公开(公告)号：US20080131259A1
公开(公告)日：2008-06-05
申请号：US11565176
申请日：2006-11-30
申请人： Ching-Pang Lee , Eric Alan Estill , James Harvey Laflen , Katherine Jaynetorrence Andersen
发明人： Ching-Pang Lee , Eric Alan Estill , James Harvey Laflen , Katherine Jaynetorrence Andersen
IPC分类号： F01D25/12
CPC分类号： F01D11/24 , F05D2240/11 , Y02T50/671
摘要： A method for cooling a shroud segment of a gas turbine engine is provided. The method includes providing a turbine shroud assembly including a shroud segment having an inner surface and a leading edge that is substantially perpendicular to the inner surface, and coupling a turbine nozzle to the turbine shroud segment such that a gap is defined between an aft edge of an outer band of the turbine nozzle and the leading edge. The method also includes directing cooling air into the gap, and directing the cooling air in the gap through at least one cooling hole extending between the leading edge and the inner surface.
摘要翻译：提供了一种用于冷却燃气涡轮发动机的护罩部分的方法。该方法包括提供一种涡轮机护罩组件，其包括具有内表面和大致垂直于内表面的前缘的护罩区段，以及将涡轮喷嘴连接到涡轮机护罩区段，使得间隙限定在涡轮喷嘴的外带和前缘。该方法还包括将冷却空气引导到间隙中，以及通过在前缘和内表面之间延伸的至少一个冷却孔将间隙中的冷却空气引导。

73. 发明申请

US20080127491A1 METHOD AND SYSTEM TO FACILITATE PREFERENTIALLY DISTRIBUTED RECUPERATED FILM COOLING OF TURBINE SHROUD ASSEMBLY 有权
标题翻译：汽轮机组装优选分布式回收薄膜冷却方法与系统
公开(公告)号：US20080127491A1
公开(公告)日：2008-06-05
申请号：US11565253
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： B23P15/00 , F01D5/08
CPC分类号： F01D11/08 , F05D2240/11 , F05D2260/202 , Y02T50/671 , Y02T50/676 , Y10T29/49236
摘要： A method of assembling a gas turbine engine includes coupling a turbine shroud assembly within the gas turbine engine. The turbine shroud assembly includes a shroud segment having a leading edge defining a forward face and a radial inner surface. A turbine nozzle is coupled to the turbine shroud assembly such that a gap is defined between an aft face of an outer band of the turbine nozzle and the forward face. A plurality of recuperated cooling openings are defined through the leading edge at an oblique inlet angle with respect to a centerline of the gap and between the forward face and the radial inner surface to direct cooling fluid through the leading edge to facilitate preferential cooling of the leading edge.
摘要翻译：一种组装燃气涡轮发动机的方法包括将涡轮机罩组件联接在燃气涡轮发动机内。涡轮机罩组件包括具有限定前表面和径向内表面的前缘的护罩区段。涡轮喷嘴联接到涡轮机护罩组件，使得在涡轮喷嘴的外带的后表面和前表面之间限定间隙。多个恢复的冷却开口通过前缘以相对于间隙的中心线和前表面和径向内表面之间的倾斜入口角度定义，以将冷却流体引导通过前缘，以便于优先冷却前导边缘。

74. 发明授权

US07377746B2 Airfoil cooling circuits and method 有权
标题翻译：翼型冷却回路及方法
公开(公告)号：US07377746B2
公开(公告)日：2008-05-27
申请号：US11062001
申请日：2005-02-21
申请人： Steven Robert Brassfield , Ching-Pang Lee , Roger Lee Doughty , Richard William Jendrix , Cory Michael Williams
发明人： Steven Robert Brassfield , Ching-Pang Lee , Roger Lee Doughty , Richard William Jendrix , Cory Michael Williams
IPC分类号： F03D11/02
CPC分类号： F01D5/18 , B22C9/043 , F05D2230/21 , Y02T50/676 , Y10T29/49243 , Y10T29/49245
摘要： An airfoil is disclosed having at least first and second cast, axially-stacked internal airflow cooling circuits. Each circuit defines multiple air flow passages positioned laterally between a pressure sidewall side and a suction sidewall side of respective ones of the circuits. Each of the circuits is formed by a separate casting core. Methods of forming a axially-stacked core and an airfoil are also disclosed.
摘要翻译：公开了一种具有至少第一和第二铸造，轴向堆叠的内部气流冷却回路的翼型件。每个回路限定了多个气流通道，其横向位于各个电路的压力侧壁侧和吸力侧壁侧之间。每个电路由单独的铸造芯形成。还公开了形成轴向堆叠的芯和翼型的方法。

75. 发明申请

US20080101913A1 Plasma lifted boundary layer gas turbine engine vane 有权
标题翻译：等离子提升边界层燃气轮机发动机叶片
公开(公告)号：US20080101913A1
公开(公告)日：2008-05-01
申请号：US11591264
申请日：2006-10-31
申请人： Ching-Pang Lee , Aspi Rustom Wadia , David Glenn Cherry , Je-Chin Han
发明人： Ching-Pang Lee , Aspi Rustom Wadia , David Glenn Cherry , Je-Chin Han
IPC分类号： F04D27/02
CPC分类号： F01D5/145 , F01D9/041 , F01D17/162 , F05D2260/20 , F05D2270/17 , F05D2270/172 , Y02T50/673 , Y02T50/676 , Y10S415/914
摘要： A plasma boundary layer lifting system includes at least one gas turbine engine vane having a spanwise extending airfoil with an outer surface extending in a chordwise direction between opposite leading and trailing edges and chordwise spaced apart plasma generators for producing a plasma extending in the chordwise direction along the outer surface. Each plasma generator may include inner and outer electrodes separated by a dielectric material disposed within a spanwise extending groove in the outer surface. The airfoil may be hollow having an outer wall and the plasma generators being mounted on the outer wall. A method for operating the system includes forming a plasma extending in the chordwise direction along the outer surface of the airfoil. The method may further include operating the plasma generators in steady state or unsteady modes.
摘要翻译：等离子体边界层提升系统包括至少一个燃气涡轮发动机叶片，其具有翼展方向延伸的翼型件，其外表面沿相反的前缘和后缘之间的弦向延伸，以及弦向间隔开的等离子体发生器，用于产生沿着弦方向延伸的等离子体外表面。每个等离子体发生器可以包括由设置在外表面中的翼展方向延伸凹槽内的电介质材料隔开的内电极和外电极。翼型件可以是中空的，具有外壁，等离子体发生器安装在外壁上。用于操作该系统的方法包括形成沿着翼型的外表面沿着弦方向延伸的等离子体。该方法还可以包括以稳态或不稳定模式操作等离子体发生器。

76. 发明申请

US20080031738A1 BELL-SHAPED FAN COOLING HOLES FOR TURBINE AIRFOIL 有权
标题翻译：用于涡轮机空气的贝尔风扇风扇冷却孔
公开(公告)号：US20080031738A1
公开(公告)日：2008-02-07
申请号：US11069869
申请日：2005-03-01
申请人： Ching-Pang Lee
发明人： Ching-Pang Lee
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/18 , F05D2200/24 , F05D2250/20 , F05D2250/26 , F05D2250/292 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： A turbine airfoil a plurality of cooling holes formed in the external surface of the airfoil in fluid communication with a cooling circuit. The cooling holes have a metering section and a diffuser section opening to the external surface of the airfoil. The diffuser section has top, bottom and opposed side walls, where at least the opposed side walls and one or the other of the top and bottom walls of the diffuser section have a downstream diverging, bell-shaped configuration for achieving a flow of the cooling film from the cooling circuit with enhanced spread, enhanced attachment and less turbulence to a downstream surface of the airfoil local to each respective cooling hole.
摘要翻译：涡轮机翼型件形成在与冷却回路流体连通的翼型件的外表面中的多个冷却孔。冷却孔具有通向翼型件的外表面的计量部分和扩散部分。扩散器部分具有顶部，底部和相对的侧壁，其中至少相对的侧壁和扩散器部分的顶壁和底壁中的一个或另一个具有下游发散的钟形构造，用于实现冷却来自冷却回路的膜具有增强的扩散，增强的附着和较少的湍流到局部于每个相应的冷却孔的翼型的下游表面。

77. 发明授权

US07296973B2 Parallel serpentine cooled blade 有权
标题翻译：平行蛇形冷却叶片
公开(公告)号：US07296973B2
公开(公告)日：2007-11-20
申请号：US11294063
申请日：2005-12-05
申请人： Ching-Pang Lee , Aspi Rustom Wadia , Steven Robert Brassfield
发明人： Ching-Pang Lee , Aspi Rustom Wadia , Steven Robert Brassfield
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2250/185 , F05D2260/202 , Y02T50/673 , 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. A first serpentine circuit is disposed along the pressure sidewall. A second serpentine circuit is disposed along the suction sidewall in parallel with the first circuit. And a third impingement circuit is disposed at the leading edge forward of the first and second circuits.
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。第一蛇形电路沿着压力侧壁设置。第二蛇形电路沿着吸力侧壁与第一回路并联设置。并且第三冲击电路设置在第一和第二电路的前方的前缘。

78. 发明申请

US20070237637A1 Skewed tip hole turbine blade 有权
标题翻译：倾斜尖端孔涡轮叶片
公开(公告)号：US20070237637A1
公开(公告)日：2007-10-11
申请号：US11211391
申请日：2005-08-25
申请人： Ching-Pang Lee , Nicholas Palmer , Kevin Kirkeng
发明人： Ching-Pang Lee , Nicholas Palmer , Kevin Kirkeng
IPC分类号： F01D5/18
CPC分类号： F01D5/20 , F01D11/08 , F05D2240/307 , F05D2250/292 , F05D2250/38 , F05D2260/20 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： A turbine blade includes a hollow airfoil having a plurality of bowed tip holes extending through a tip floor thereof and skewed toward a squealer rib extending outwardly from the floor.
摘要翻译：涡轮机叶片包括具有延伸穿过其尖端底部的多个弓形尖端孔的中空翼型件，并且朝着从地板向外延伸的尖叫肋条倾斜。

79. 发明申请

US20070214795A1 Continuous real time EGT margin control 审中-公开
标题翻译：连续实时EGT保证金控制
公开(公告)号：US20070214795A1
公开(公告)日：2007-09-20
申请号：US11376507
申请日：2006-03-15
申请人： Paul Cooker , Robert Orlando , Ching-Pang Lee , Kattalaicheri Venkataramani
发明人： Paul Cooker , Robert Orlando , Ching-Pang Lee , Kattalaicheri Venkataramani
IPC分类号： F02C1/00
CPC分类号： F02K1/06 , F02C9/22 , F02C9/28 , F02K1/08 , F02K1/09 , F02K3/06 , F05D2270/112 , F05D2270/303 , F05D2270/3032
摘要： A method and system for maintaining a limiting gas temperature in a gas turbine engine working fluid flowpath by monitoring the gas temperature and adjusting one or more parameters when the gas temperature exceeds a predetermined or a calculated temperature limit during engine operation. The parameters include one or more of a group of engine parameters including high and low pressure turbine nozzle flow areas, fan and core flow areas, and a rotor speed. The one or more parameters are adjusted to lower the gas temperature to below the temperature limit during engine operation. The limiting gas temperature may be a turbine exhaust gas temperature such as a high pressure turbine exhaust gas temperature. The turbine nozzle flow areas may be adjusted with variable nozzle vanes and the fan and core exhaust nozzle flow areas with a translatable fan nozzle cowling and a translatable core nozzle plug, respectively.
摘要翻译：一种用于通过监测气体温度并在发动机运行期间当气体温度超过预定或计算的温度极限时调节一个或多个参数来维持燃气涡轮发动机工作流体流路中的限制气体温度的方法和系统。这些参数包括一组发动机参数中的一个或多个，包括高压和低压涡轮喷嘴流动区域，风扇和核心流动区域以及转子速度。调节一个或多个参数以在发动机运行期间将气体温度降低到温度极限以下。限制气体温度可以是涡轮机废气温度，例如高压汽轮机废气温度。涡轮喷嘴流动面积可以分别用可变喷嘴叶片和风扇和核心排气喷嘴流动区域调节，其中分别具有可平移的风扇喷嘴罩和可平移的芯喷嘴塞。

80. 发明申请

US20070128034A1 Zigzag cooled turbine airfoil 有权
公开(公告)号：US20070128034A1
公开(公告)日：2007-06-07
申请号：US11294218
申请日：2005-12-05
申请人： Ching-Pang Lee , Aspi Wadia , Steven Brassfield
发明人： Ching-Pang Lee , Aspi Wadia , Steven Brassfield
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/121 , F05D2240/303 , F05D2250/185 , F05D2260/201 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A turbine airfoil includes pressure and suction sidewalls spaced apart to define flow channels extending in span and separated by ribs. Side channels are disposed along one sidewall and spaced from the opposite sidewall by the ribs, and a mid channel bridges the sidewalls. The side and mid channels are arranged in a zigzag serpentine cooling circuit alternating therebetween for transferring heat from the sidewall into the mid channel.

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