-
21.发明申请公开(公告)号：US20150184518A1
公开(公告)日：2015-07-02
申请号：US14140593
申请日：2013-12-26
申请人： Ching-Pang Lee
发明人： Ching-Pang Lee
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 having wavy side edges that form a jagged edge As such, the nonlinear longitudinal axis 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 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浪形侧边缘的肋限定。因此，后缘出口槽的非线性纵向轴线减小有效流动面积，产生冲击和湍流以增加热传递并提供足够的机械 强度更好的铸造产量而不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和熔模铸造形成。
-
公开(公告)号：US09068461B2
公开(公告)日：2015-06-30
申请号：US13212263
申请日：2011-08-18
IPC分类号： F01D5/08
CPC分类号： F01D5/087
摘要： A turbine rotor body having at least one inlet orifice in fluid communication with a pre-swirl system such that the inlet orifice receives cooling fluids from the pre-swirl system is disclosed. The inlet orifice may be configured to reduce the relative velocity loss associated with cooling fluids entering the inlet orifice in the rotor, thereby availing the cooling system to the efficiencies inherent in pre-swirling the cooling fluids to a velocity that is greater than a rotational velocity of the turbine rotor body. As such, the system is capable of taking advantage of the additional temperature and work benefits associated with using the pre-swirled cooling fluids having a rotational speed greater than the turbine rotor body.
摘要翻译： 一种涡轮转子体，具有至少一个入口孔，其与预旋系统流体连通，使得入口孔接收来自预涡流系统的冷却流体。 入口孔口可以被配置为减小与进入转子中的入口孔口的冷却流体相关联的相对速度损失，从而将冷却系统利用到将冷却流体预旋转的固有效率大于旋转速度 的涡轮转子体。 因此，该系统能够利用与使用具有大于涡轮转子体的转速的预旋涡冷却流体相关联的附加温度和工作效益。
-
公开(公告)号：US09062557B2
公开(公告)日：2015-06-23
申请号：US13226547
申请日：2011-09-07
申请人： Kok-Mun Tham , Ching-Pang Lee , Abdullatif M. Chehab , Gm Salam Azad , Shantanu P. Mhetras , Manjit Shivanand , Vincent P. Laurello , Christopher Rawlings
发明人： Kok-Mun Tham , Ching-Pang Lee , Abdullatif M. Chehab , Gm Salam Azad , Shantanu P. Mhetras , Manjit Shivanand , Vincent P. Laurello , Christopher Rawlings
CPC分类号： F01D11/001 , F01D11/04
摘要： A gas turbine having rotor discs (9), a disc cavity (13) and a stator stage (25) extending to the disc cavity (13). Seal housing flanges (43, 44) extend from a seal housing (29) of the stator stage (25). Rotor flanges (41i, 41o) extend from a rotor disk (9-1). An inner rotor flange (41i) and first seal housing flange (43) are inward from a second seal housing flange (44). One rotor flange (41o) is outward from the second seal housing flange (44). The inner rotor flange (41i) and first seal housing flange (43) extend toward one another to limit movement of main gas flow (17). An inlet (47) injects air (50) between the outward rotor flange (41o) and second seal housing flange (44).
摘要翻译： 一种具有转子盘（9），延伸到盘腔（13）的盘腔（13）和定子级（25）的燃气轮机。 密封壳体凸缘（43,44）从定子台（25）的密封壳体（29）延伸。 转子凸缘（41i，41o）从转子盘（9-1）延伸。 内转子凸缘（41i）和第一密封壳体凸缘（43）从第二密封壳体凸缘（44）向内。 一个转子凸缘（41o）从第二密封壳体凸缘（44）向外。 内转子凸缘（41i）和第一密封壳体凸缘（43）朝向彼此延伸以限制主气流（17）的移动。 入口（47）在外转子凸缘（41o）和第二密封壳体凸缘（44）之间注入空气（50）。
-
24.发明授权Trailing edge cooling using angled impingement on surface enhanced with cast chevron arrangements 有权使用倾斜的冲击在表面上的后缘冷却通过铸造人字形布置增强公开(公告)号：US09039371B2
公开(公告)日：2015-05-26
申请号：US14068070
申请日：2013-10-31
CPC分类号： F01D5/187 , F01D9/02 , F05D2240/122 , F05D2240/304 , F05D2260/201 , F05D2260/2212
摘要： A gas turbine engine component, including: a pressure side (12) having an interior surface (34); a suction side (14) having an interior surface (36); a trailing edge portion (30); and a plurality of suction side and pressure side impingement orifices (24) disposed in the trailing edge portion (30). Each suction side impingement orifice is configured to direct an impingement jet (48) at an acute angle (52) onto a target area (60) that encompasses a tip (140) of a chevron (122) within a chevron arrangement (120) formed in the suction side interior surface. Each pressure side impingement orifice is configured to direct an impingement jet at an acute angle onto an elongated target area that encompasses a tip of a chevron within a chevron arrangement formed in the pressure side interior surface.
摘要翻译： 一种燃气涡轮发动机部件，包括：具有内表面（34）的压力侧（12）; 吸入侧（14），其具有内表面（36）; 后缘部分（30）; 以及设置在后缘部分（30）中的多个吸力侧和压力侧冲击孔（24）。 每个吸入侧冲击孔构造成将锐角（52）的冲击射流（48）引导到目标区域（60）上，所述目标区域包围形成的人字形布置（120）内的人字形（122）的尖端（140） 在吸力侧内表面。 每个压力侧冲击孔构造成将冲击射流以锐角引导到细长的目标区域上，所述细长目标区域包含形成在压力侧内表面中的人字形布置中的人字形尖端。
-
公开(公告)号：US08973372B2
公开(公告)日：2015-03-10
申请号：US13603699
申请日：2012-09-05
申请人： Ching-Pang Lee , Evan C. Landrum , Jiping Zhang
发明人： Ching-Pang Lee , Evan C. Landrum , Jiping Zhang
摘要： A shell air recirculation system for use in a gas turbine engine includes one or more outlet ports located at a bottom wall section of an engine casing wall and one or more inlet ports located at a top wall section of the engine casing wall. The system further includes a piping system that provides fluid communication between the outlet port(s) and the inlet port(s), a blower for extracting air from a combustor shell through the outlet port(s) and for conveying the extracted air to the inlet port(s), and a valve system for selectively allowing and preventing air from passing through the piping system. The system operates during less than full load operation of the engine to circulate air within the combustor shell but is not operational during full load operation of the engine.
摘要翻译： 用于燃气涡轮发动机的壳体空气再循环系统包括位于发动机壳体壁的底壁部分和位于发动机壳体壁的顶壁部分的一个或多个入口的一个或多个出口。 该系统还包括一个在出口和入口之间提供流体连通的管道系统，用于从燃烧器壳体通过出口提取空气并将提取的空气输送到 进气口和用于选择性地允许和防止空气通过管道系统的阀系统。 该系统在发动机小于满载运行期间运行，以使燃烧器壳体内的空气循环，但是在发动机满载运行期间不起作用。
-
26.发明授权公开(公告)号：US08944763B2
公开(公告)日：2015-02-03
申请号：US13212282
申请日：2011-08-18
申请人： Ching-Pang Lee
发明人： Ching-Pang Lee
CPC分类号： F01D5/087 , F01D5/187 , F05D2250/185 , F05D2260/202 , F05D2260/2212
摘要： A cooling system for a turbine blade of a turbine engine having a bifurcated mid-chord cooling chamber for reducing the temperature of the blade. The bifurcated mid-chord cooling chamber may be formed from a pressure side serpentine cooling channel and a suction side serpentine cooling channel with cooling fluids passing through the pressure side serpentine cooling channel in a direction from the trailing edge toward the leading edge and in an opposite direction through the suction side serpentine cooling channel. The pressure side and suction side serpentine cooling channels may flow counter to each other, thereby yielding a more uniform temperature distribution than conventional serpentine cooling channels.
摘要翻译： 一种用于涡轮发动机的涡轮叶片的冷却系统，其具有用于降低叶片温度的分叉中和冷却室。 分叉中弦冷却室可以由压力侧蛇形冷却通道和吸入侧蛇形冷却通道形成，其中冷却流体沿着从后缘朝向前缘的方向通过压力侧蛇形冷却通道，并且在相反的 方向通过吸力侧蛇形冷却通道。 压力侧和吸力侧蛇形冷却通道可以相互流动，从而产生比常规蛇形冷却通道更均匀的温度分布。
-
27.发明授权Vane outer support ring with no forward hook in a compressor section of a gas turbine engine 有权在燃气涡轮发动机的压缩机部分中没有前挂钩的叶片外支撑环公开(公告)号：US08939717B1
公开(公告)日：2015-01-27
申请号：US14063153
申请日：2013-10-25
CPC分类号： F01D25/246 , B23P6/005 , F01D9/042 , F05D2230/80 , F05D2250/61
摘要： A support ring for a row of vanes in an engine section of a gas turbine engine includes an annular main body portion to which a row of vanes is affixed for providing structural support for the vanes in the engine section, and an aft hook extending from an aft side of the main body portion with reference to a direction of air flow through the engine section. The aft hook is coupled to an outer engine casing for structurally supporting the support ring in the engine section. The support ring does not include a forward hook having a flange that extends axially from a forward or aft side of the forward hook with reference to the direction of air flow through the engine section.
摘要翻译： 在燃气涡轮发动机的发动机部分中的一排叶片的支撑环包括环形主体部分，一排叶片固定到该环形主体部分，用于为发动机部分中的叶片提供结构支撑，以及从一个 相对于通过发动机部分的空气流动的方向，主体部分的后侧。 后钩联接到外发动机壳体，用于在发动机部分中结构地支撑支撑环。 支撑环不包括前挂钩，其具有相对于通过发动机部分的空气流的方向具有从前钩的前侧或后侧轴向延伸的凸缘。
-
28.发明授权Cooling module design and method for cooling components of a gas turbine system 有权用于冷却燃气轮机系统组件的冷却模块设计和方法公开(公告)号：US08894363B2
公开(公告)日：2014-11-25
申请号：US13023716
申请日：2011-02-09
IPC分类号： F01D5/18
CPC分类号： F01D5/184 , F01D5/186 , F01D5/187 , F05D2220/32 , F05D2230/51 , F05D2240/30 , F05D2240/40
摘要： A cooling arrangement in a gas turbine system (120). The arrangement includes a plurality of flow network units (208) to transfer heat to cooling fluid, at least one unit including first (218), second (220), and third (222) flow sections between openings (64a) in a first wall (66) and an opening in a second wall (68) to pass cooling fluid through the walls. The first section includes first flow paths, between the openings in the first wall and the second section, extending to the second section. The third section includes third flow paths, between the second section and the opening in the second wall, to effect flow of cooling fluid. The second section includes one or more cooling fluid flow paths between the first section and the third section. The number of flow paths in the second section is fewer than the number of first flow paths and fewer than the number of third flow paths.
摘要翻译： 燃气轮机系统（120）中的冷却装置。 该装置包括多个流动网络单元（208），用于将热量传递到冷却流体;至少一个单元，包括在第一壁中的开口（64a）之间的第一（218），第二（220）和第三（222） （66）和第二壁（68）中的开口以使冷却流体通过壁。 第一部分包括在第一壁的开口和第二部分之间延伸到第二部分的第一流动路径。 第三部分包括在第二部分和第二壁中的开口之间的第三流动路径，以实现冷却流体的流动。 第二部分包括在第一部分和第三部分之间的一个或多个冷却流体流动路径。 第二部分中的流动路径的数量少于第一流动路径的数量，并且少于第三流动路径的数量。
-
公开(公告)号：US08894359B2
公开(公告)日：2014-11-25
申请号：US13314311
申请日：2011-12-08
申请人： Mrinal Munshi , John Finneran , Ching-Pang Lee , Yevgeniy Shteyman , Daryl Graber , Matthew R. Porter , Jonathan M. Leagon
发明人： Mrinal Munshi , John Finneran , Ching-Pang Lee , Yevgeniy Shteyman , Daryl Graber , Matthew R. Porter , Jonathan M. Leagon
CPC分类号： F01D25/08
摘要： A thermal barrier/cooling system for controlling a temperature of an outer case of a gas turbine engine. The thermal barrier/cooling system includes an internal insulating layer supported on an inner case surface, the internal insulating layer extending circumferentially along the inner case surface and providing a thermal resistance to radiated energy from structure located radially inwardly from the outer case. The thermal barrier/cooling system further includes a convective cooling channel defined by a panel structure located in radially spaced relation to an outer case surface of the outer case and extending around the circumference of the outer case surface. The convective cooling channel forms a flow path for an ambient air flow cooling the outer case surface.
摘要翻译： 一种用于控制燃气涡轮发动机的外壳的温度的隔热/冷却系统。 所述隔热/冷却系统包括支撑在内壳体表面上的内部绝缘层，所述内部绝缘层沿着所述内壳表面周向延伸，并且提供对从外壳径向向内定位的结构的辐射能的热阻。 隔热/冷却系统还包括由面板结构限定的对流冷却通道，所述面板结构位于与外壳的外壳表面径向间隔开的关系中并围绕外壳表面的圆周延伸。 对流冷却通道形成用于冷却外壳表面的环境空气流的流路。
-
公开(公告)号：US08864452B2
公开(公告)日：2014-10-21
申请号：US13212273
申请日：2011-08-18
申请人： Kok-Mun Tham , Ching-Pang Lee
发明人： Kok-Mun Tham , Ching-Pang Lee
IPC分类号： F01D5/14
CPC分类号： F01D5/145 , F01D5/143 , F05D2240/80
摘要： In a gas turbine engine, a flow directing member includes a platform supported on a rotor, a radially facing endwall, at least one axial surface extending radially inwardly from a junction with the endwall, an airfoil extending radially outwardly from the endwall, and a fluid flow directing feature. The fluid flow directing feature includes a groove extending axially into the axial surface and has radially inner and outer groove ends. The outer groove end defines an axially extending notch in the junction between the axial surface and the endwall and forms an opening in the endwall for directing a cooling fluid to the endwall. The groove further includes a first groove wall extending from the inner groove end to the outer groove end, and a second groove wall opposed from the first groove wall and extending from the inner groove end to the outer groove end.
摘要翻译： 在燃气涡轮发动机中，导流构件包括支撑在转子上的平台，径向面向的端壁，从与端壁的接合处径向向内延伸的至少一个轴向表面，从端壁径向向外延伸的翼型件和流体 流导向功能。 流体流动导向特征包括沿轴向延伸并且具有径向内部和外部凹槽端部的凹槽。 外槽端部在轴向表面和端壁之间的连接处限定轴向延伸的凹口，并在端壁中形成用于将冷却流体引导到端壁的开口。 所述凹槽还包括从所述内槽端延伸到所述外槽端部的第一槽壁和与所述第一槽壁相对并从所述内槽端部延伸到所述外槽端部的第二槽壁。
-
-
-
-
-
-
-
-
-
搜索结果
519 条记录 (耗时 0.032 秒)