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1. 发明授权

US09228437B1 Turbine airfoil with pressure side trailing edge cooling slots 有权
标题翻译：涡轮机翼与压力侧后缘冷却槽
公开(公告)号：US09228437B1
公开(公告)日：2016-01-05
申请号：US13427250
申请日：2012-03-22
申请人： George Liang
发明人： George Liang
IPC分类号： F01D5/18 , F01D5/08 , B23P15/04
CPC分类号： F01D5/087 , B23P15/02 , B23P15/04 , F01D5/187 , F05D2230/21 , F05D2230/61 , F05D2240/304
摘要： An air cooled turbine blade with a trailing edge cooling circuit that is formed by casting the airfoil with a pressure side trailing edge lip being oversized, and then machining away material from the pressure side wall to leave a pressure side bleed slot with a smaller (t/s) ratio than can be formed by casting alone. In another embodiment, the airfoil is cast with a trailing edge exit hole, and then the material on the pressure side wall in the trailing edge region is machined away to leave a pressure side bleed slot instead of an exit hole.
摘要翻译：具有后缘冷却回路的空气冷却涡轮机叶片，该后缘冷却回路通过将压力侧后缘加上翼型而形成，然后从压力侧壁加工材料以留下具有较小的（t）的压力侧排放槽 / s）比可以通过铸造单独形成。在另一个实施例中，翼型件具有后缘出口孔，然后在后缘区域中的压力侧壁上的材料被加工而离开压力侧泄放槽而不是出口孔。

2. 发明授权

US08827647B1 Turbine blade with root section cooling 有权
标题翻译：涡轮叶片根部冷却
公开(公告)号：US08827647B1
公开(公告)日：2014-09-09
申请号：US12822226
申请日：2010-06-24
申请人： George Liang
发明人： George Liang
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/81 , F05D2260/201
摘要： A turbine rotor blade with a four-pass aft flowing serpentine flow cooling circuit with a first leg located along the leading edge and the fourth leg located along the trailing edge region, and with two exit slots connected to the fourth leg with one exit slot opening on the trailing edge just above the platform and the second exit slot opening just below the platform.
摘要翻译：一种涡轮转子叶片，具有四通后流动的蛇形流冷却回路，其第一支腿沿前缘定位，第四腿沿着后缘区域定位，并且两个出口槽连接到第四腿部，一个出口槽口在平台的正上方的后缘，并且位于平台正下方的第二出口槽开口。

3. 发明授权

US08777571B1 Turbine airfoil with curved diffusion film cooling slot 有权
标题翻译：具有弯曲扩散膜冷却槽的涡轮翼型
公开(公告)号：US08777571B1
公开(公告)日：2014-07-15
申请号：US13316485
申请日：2011-12-10
申请人： George Liang
发明人： George Liang
IPC分类号： F01D5/20
CPC分类号： F01D5/187 , F05D2240/303 , F05D2260/202 , F05D2260/205
摘要： An air cooled turbine airfoil with a leading edge region having rows of diffusion slots opening onto the airfoil surface. Each diffusion slot is connected to a plurality of metering and diffusion holes that meter the cooling air flow and provide for a first diffusion of the cooling air. The metering holes and diffusion holes are angled in order to improve the cooling effectiveness of the passages. The metering and diffusion holes and diffusion slots are formed from a metal printing process that can produce features that cannot be formed from an investment casting process that uses a ceramic core.
摘要翻译：一种具有前缘区域的空气冷却涡轮机翼型件，其具有在翼型件表面上开口的一排扩散槽。每个扩散槽连接到多个计量和扩散孔，其计量冷却空气流并提供冷却空气的第一扩散。计量孔和扩散孔成角度，以提高通道的冷却效果。计量和扩散孔和扩散槽由金属印刷工艺形成，该工艺可产生不能使用陶瓷芯的熔模铸造工艺形成的特征。

4. 发明授权

US08777570B1 Turbine vane with film cooling slots 失效
标题翻译：涡轮叶片带薄膜冷却槽
公开(公告)号：US08777570B1
公开(公告)日：2014-07-15
申请号：US12757226
申请日：2010-04-09
申请人： George Liang
发明人： George Liang
IPC分类号： F01D5/08
CPC分类号： F01D5/187 , F01D5/186 , F05D2240/12 , F05D2240/81 , F05D2250/185
摘要： A stator vane with endwalls having film cooling diffusion slots that open onto the hot gas surface. Each diffusion slot is formed as a row of one or more separated diffusion slots each having a serpentine flow channel and one or more metering inlet holes to supply spent cooling air from an impingement chamber to the diffusion slots. The metering inlet holes meter the flow of cooling air into the serpentine channels, the serpentine channels provide convection cooling for the endwalls, and the diffusion slots diffuse the cooling air into a layer of film cooling air onto the hot gas surface of the endwalls.
摘要翻译：具有端壁的定子叶片具有通向热气体表面上的薄膜冷却扩散槽。每个扩散槽形成为一排一个或多个分离的扩散槽，每个扩散狭槽具有蛇形流动通道和一个或多个计量入口孔，以将消耗的冷却空气从冲击室提供到扩散槽。计量入口孔测量冷却空气进入蛇形通道的流量，蛇形通道为端壁提供对流冷却，扩散槽将冷却空气扩散到一层薄膜冷却空气到端壁的热气表面上。

5. 发明授权

US08721285B2 Turbine blade with incremental serpentine cooling channels beneath a thermal skin 失效
标题翻译：涡轮叶片，带有热皮肤下的增量蛇形冷却通道
公开(公告)号：US08721285B2
公开(公告)日：2014-05-13
申请号：US12397766
申请日：2009-03-04
申请人： George Liang
发明人： George Liang
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F01D5/187 , F05D2250/185 , F05D2260/22141
摘要： A turbine blade having an internal cooling system with incremental serpentine cooling channels in near walls forming an outer surface of the turbine blade is disclosed. The turbine blade may be formed from an internal structural spar that is covered with a thermal skin. The incremental serpentine cooling channels may be cut into the outer surface of the spar to which the thermal skin may be attached. The incremental serpentine cooling channels may be formed from two or more serpentine cooling channels aligned along an axis that extends generally spanwise throughout the turbine blade. A row of incremental serpentine cooling channels may extend from a root to a tip of the blade, but a single incremental cooling channel does not.
摘要翻译：公开了一种具有内部冷却系统的涡轮机叶片，该内部冷却系统在形成涡轮机叶片的外表面的近壁处具有增量的蛇形冷却通道。涡轮机叶片可以由内部结构的翼梁形成，内部的结构翼梁被热的皮肤覆盖。增量蛇形冷却通道可以被切割到可以附着热皮肤的翼梁的外表面。增量蛇形冷却通道可以由两个或更多个沿着轴线对齐的蛇形冷却通道形成，该轴线大致跨越涡轮机叶片。一排增量蛇形冷却通道可以从根部延伸到刀片的尖端，但是单个增量冷却通道不会。

6. 发明授权

US08668437B1 Turbine engine cooling fluid feed system 失效
标题翻译：涡轮发动机冷却液进料系统
公开(公告)号：US08668437B1
公开(公告)日：2014-03-11
申请号：US12691529
申请日：2010-01-21
申请人： George Liang
发明人： George Liang
IPC分类号： F01D5/14
CPC分类号： F01D5/14 , F01D5/082
摘要： A cooling fluid feed system for a turbine engine for directing cooling fluids from a compressor, through one or more impellers, and into row one turbine vanes and one or more rows of turbine blades for increasing the cooling capacity of the turbine vanes and blades. Such a configuration increases cooling capacity, which in turn increases the capacity for growth within the turbine engine, creates a larger cooling fluid to gas side pressure differential and reduces amount of bleed off of cooling fluids from the compressor, thereby increasing efficiency of the turbine engine.
摘要翻译：一种用于涡轮发动机的冷却流体进料系统，用于将来自压缩机的冷却流体引导通过一个或多个叶轮，以及一排涡轮叶片和一排或多排涡轮机叶片，用于增加涡轮叶片和叶片的冷却能力。这种配置增加了冷却能力，这又增加了涡轮发动机内的增长能力，产生了更大的冷却流体到气体侧压力差并且减少了来自压缩机的冷却流体的泄漏量，从而提高了涡轮发动机的效率。

7. 发明授权

US08632298B1 Turbine vane with endwall cooling 有权
标题翻译：涡轮叶片与端壁冷却
公开(公告)号：US08632298B1
公开(公告)日：2014-01-21
申请号：US13052318
申请日：2011-03-21
申请人： George Liang
发明人： George Liang
IPC分类号： F01D5/08
CPC分类号： F01D9/041 , F01D25/12 , F05D2240/81 , F05D2260/201 , F05D2260/202
摘要： A turbine stator vane with an endwall cooling circuit that includes a first ten-pass serpentine flow cooling circuit and a second ten-pass serpentine flow cooling circuit. Each serpentine circuit is connected to cooling air feed holes supplied from an endwall impingement cavity, where cooling air serpentines along the leading edge section of the endwall, along the two mate faces, and then serpentines along the trailing edge section where the cooling air is discharged from exit holes spaced along the trailing edge side of the endwall.
摘要翻译：一种具有端壁冷却回路的涡轮机定子叶片，其包括第一十通蛇形流冷却回路和第二十通蛇形流冷却回路。每个蛇形回路连接到从端壁冲击腔提供的冷却空气供给孔，其中冷却空气沿着端壁的前缘部分沿着两个配合面沿着前缘部分蛇行，然后沿着冷却空气排放的后缘部分蛇形从沿着端壁的后缘侧间隔开的出口孔。

8. 发明授权

US08628294B1 Turbine stator vane with purge air channel 有权
标题翻译：具有吹扫空气通道的涡轮定子叶片
公开(公告)号：US08628294B1
公开(公告)日：2014-01-14
申请号：US13111106
申请日：2011-05-19
申请人： George Liang
发明人： George Liang
IPC分类号： F01D9/02 , F01D25/08
CPC分类号： F01D5/187 , F01D9/041 , F01D25/12
摘要： A stator vane for an industrial turbine, the vane includes a serpentine flow cooling circuit for cooling of the airfoil, and a separate purge air channel to supply purge air to the rim cavities. The purge channel is formed as a separate channel from the serpentine flow channels so that the purge air is not heated by the hot metal and has smooth surfaces so that pressure losses is minimal.
摘要翻译：用于工业涡轮机的定子叶片，叶片包括用于冷却翼型件的蛇形流冷却回路，以及用于向边缘空腔供应吹扫空气的单独吹扫空气通道。净化通道形成为与蛇形流动通道的单独通道，使得吹扫空气不被热金属加热并且具有平滑的表面，使得压力损失最小。

9. 发明授权

US08596962B1 BOAS segment for a turbine 失效
标题翻译：用于涡轮机的BOAS段
公开(公告)号：US08596962B1
公开(公告)日：2013-12-03
申请号：US13052325
申请日：2011-03-21
申请人： George Liang
发明人： George Liang
IPC分类号： F04D29/58
CPC分类号： F01D11/08 , F01D11/24 , F05D2240/11 , F05D2260/22141
摘要： A BOAS segment for a turbine includes an impingement cavity with circular cooling air supply holes adjacent to a leading edge side of the cavity and is connected to main body axial cooling holes that open onto the trailing edge side of the BOAS segment. Cooling supply holes are located at the four corners of the impingement cavity and are connected to multiple cooling holes that open onto both edges of the segment in that corner. Thin metering cooling slots are positioned along the mate face sides in the cavity and are each connected to multiple cooling holes that discharge cooling air onto the mate face edges.
摘要翻译：用于涡轮机的BOAS部分包括冲击腔，其具有与空腔的前缘侧相邻的圆形冷却空气供应孔，并且连接到主体轴向冷却孔，所述主体轴向冷却孔打开到BOAS段的后缘侧。冷却供应孔位于冲击腔的四个角处，并连接到多个冷却孔，该冷却孔打开该角落中的段的两个边缘。薄的计量冷却槽沿着空腔中的配合面侧定位，并且各自连接到多个冷却孔，其将冷却空气排出到配合面的边缘上。

10. 发明授权

US08500401B1 Turbine blade with counter flowing near wall cooling channels 有权
标题翻译：涡轮叶片具有反流道，靠近壁冷却通道
公开(公告)号：US08500401B1
公开(公告)日：2013-08-06
申请号：US13539720
申请日：2012-07-02
申请人： George Liang
发明人： George Liang
IPC分类号： F01D5/08 , F01D5/18
CPC分类号： F01D5/186 , F05D2260/202 , F05D2260/205
摘要： A turbine rotor blade with counter flowing near wall cooling channels that includes an outer spanwise flowing near wall cooling channel and an inner chordwise flowing near wall cooling channel connected in series and with an arrangement of pedestals to produce turbulent flow. Cooling air form the spanwise flow channels flows through a blade tip floor cooling channel and then into a collection cavity, and then through impingement cooling holes in the leading edge region and into the chordwise channels before discharging out exit holes on both sides of the blade. An arrangement of pedestals forms 90 degree flow paths through the near wall cooling channels.
摘要翻译：涡轮转子叶片，其具有靠近壁冷却通道的逆流，该涡流转子叶片包括外翼展流动的近壁冷却通道和沿着串联连接的靠近壁冷却通道的内部弦流流动，并且具有基座的布置以产生湍流。形成翼展式流动通道的冷却空气流过叶片顶部地板冷却通道，然后流入收集空腔，然后通过冲击冷却孔在前缘区域中并进入弦向通道，然后排出叶片两侧的出口孔。基座的布置形成90度的通过近壁冷却通道的流路。

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