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61. 发明申请

US20150093281A1 Method of Creating a Surface Texture 审中-公开
标题翻译：创建表面纹理的方法
公开(公告)号：US20150093281A1
公开(公告)日：2015-04-02
申请号：US14039336
申请日：2013-09-27
申请人： Pratt & Whitney Canada Corp.
发明人： Marc CAMPOMANES , Orlando SCALZO , Guillaume POITRAS
IPC分类号： B22F5/00 , B22F5/10 , B22F3/12
CPC分类号： B22F5/009 , B22F3/12 , B22F3/225 , B22F3/24 , B22F5/10 , B22F2005/005 , B22F2998/10 , B22F2999/00 , C04B35/638 , C04B2235/5436 , C04B2235/5445 , C04B2235/6022 , C04B2235/665 , C04B2235/945 , C04B2235/963 , C04B2237/62 , C04B2237/64 , F01D11/24 , F05D2240/11 , F05D2250/221 , F05D2250/294 , F05D2260/201 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141 , B22F3/1021 , B22F2003/241 , B22F2003/245 , B22F2003/248 , B22F2202/11
摘要： A method of creating a texture on at least one surface of a part is disclosed. The part is molded from a feedstock including a powder remaining solid during molding and a binder, and solidified. Then, a physical state of the binder is changed in only a predetermined portion of each surface of the part to be textured. The texture is then created from the predetermined portion by debinding and sintering the part.
摘要翻译：公开了在零件的至少一个表面上产生纹理的方法。该部件由包括在模制过程中保留固体的粉末和粘合剂的原料模制并固化。然后，粘合剂的物理状态仅在待纹理部分的每个表面的预定部分中改变。然后通过脱模和烧结该部件从预定部分产生纹理。

62. 发明申请

US20150086381A1 INTERNALLY COOLED AIRFOIL 有权
标题翻译：内部冷却空气
公开(公告)号：US20150086381A1
公开(公告)日：2015-03-26
申请号：US14037948
申请日：2013-09-26
申请人： Pratt & Whitney Canada Corp.
发明人： MICHAEL PAPPLE
IPC分类号： F01D5/18
CPC分类号： F01D9/065 , F01D5/187 , F05D2260/2212 , F05D2260/22141
摘要： An internally cooled airfoil for a gas turbine engine has a hollow airfoil body including pressure and suction sidewalls defining a cooling passage therebetween. A combination of pedestal and trip-strips are used in the cooling passage to enhance heat transfer while minimizing the coolant pressure drop across these features.
摘要翻译：用于燃气涡轮发动机的内部冷却翼型件具有中空翼型件本体，其包括限定其间的冷却通道的压力和抽吸侧壁。在冷却通道中使用基座和跳闸条的组合以增强热传递，同时最小化穿过这些特征的冷却剂压降。

63. 发明授权

US08870537B2 Near-wall serpentine cooled turbine airfoil 有权
标题翻译：近壁蛇形冷却涡轮机翼型
公开(公告)号：US08870537B2
公开(公告)日：2014-10-28
申请号：US13942782
申请日：2013-07-16
申请人： Mikro Systems, Inc.
发明人： Ching-Pang Lee
IPC分类号： F01D5/18 , F01D25/12
CPC分类号： F01D25/12 , F01D5/187 , F05D2250/185 , F05D2260/202 , F05D2260/22141
摘要： A serpentine coolant flow path is formed by inner walls in a cavity between pressure and suction side walls of a turbine airfoil, the cavity partitioned by one or more transverse partitions into a plurality of continuous serpentine cooling flow streams each having a respective coolant inlet.
摘要翻译：蛇形冷却剂流动路径由涡轮机翼型的压力和吸入侧壁之间的空腔中的内壁形成，空腔由一个或多个横向隔板分隔成多个连续的蛇形冷却流，每个具有相应的冷却剂入口。

64. 发明申请

US20140212269A1 COOLING FOR A FLUID FLOW MACHINE 审中-公开
标题翻译：冷却液流动机
公开(公告)号：US20140212269A1
公开(公告)日：2014-07-31
申请号：US14239139
申请日：2012-08-02
申请人： Christoph Kastner , Rudolf Potter
发明人： Christoph Kastner , Rudolf Potter
IPC分类号： F01D3/04
CPC分类号： F01D3/04 , F01D3/02 , F01D25/26 , F02C7/141 , F05D2220/31 , F05D2260/213 , F05D2260/2214 , F05D2260/22141 , F05D2260/2322
摘要： A fluid flow machine, in particular a steam turbine, is provided having a piston-equalizing line which conducts a vapour from a fresh vapour region of a second flow duct to a thrust-equalizing piston, wherein the surface of the piston-equalizing line is enlarged, and wherein the inner surface of the piston-equalizing line is enlarged.
摘要翻译：提供了一种流体流动机，特别是蒸汽涡轮机，其具有将来自第二流动管道的新鲜蒸汽区域的蒸汽传导到推力均衡活塞的活塞均衡管线，其中活塞均衡管线的表面是并且其中活塞均衡线的内表面被扩大。

65. 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。

66. 发明申请

US20140127013A1 GAS TURBINE ENGINE AIRFOIL COOLING CIRCUIT 有权
标题翻译：气体涡轮发动机空气冷却电路
公开(公告)号：US20140127013A1
公开(公告)日：2014-05-08
申请号：US13627072
申请日：2012-09-26
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Brandon W. Spangler , Mark F. Zelesky , Edwin Otero
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , F01D5/187 , F05D2260/202 , F05D2260/205 , F05D2260/22141 , Y02T50/676
摘要： A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that extends between a leading edge, a trailing edge, a pressure side wall and a suction side wall. A cooling circuit is disposed inside of the airfoil. The cooling circuit includes a first core cavity that radially extends inside of the airfoil. A first axial skin core is in fluid communication with the first core cavity at a first location of the first axial skin core and a second core cavity is in fluid communication with the first axial skin core at a second location of the first axial skin core.
摘要翻译：根据本公开的示例性方面的用于燃气涡轮发动机的部件尤其包括在前缘，后缘，压力侧壁和吸力侧壁之间延伸的翼型件。冷却回路设置在翼型的内部。冷却回路包括在翼型件内径向延伸的第一芯腔。第一轴向皮肤芯在第一轴向皮肤芯的第一位置处与第一芯腔流体连通，并且第二芯腔在第一轴向皮肤芯的第二位置处与第一轴向皮肤芯流体连通。

67. 发明授权

US08651805B2 Hot gas path component cooling system 有权
标题翻译：热气路组件冷却系统
公开(公告)号：US08651805B2
公开(公告)日：2014-02-18
申请号：US12765372
申请日：2010-04-22
申请人： Benjamin Paul Lacy , Ronald Scott Bunker , Gary Michael Itzel
发明人： Benjamin Paul Lacy , Ronald Scott Bunker , Gary Michael Itzel
IPC分类号： F01D25/14
CPC分类号： F01D25/12 , F01D5/186 , F01D5/187 , F02C7/12 , F05D2230/11 , F05D2230/13 , F05D2230/313 , F05D2230/314 , F05D2230/90 , F05D2260/201 , F05D2260/202 , F05D2260/22141
摘要： A cooling system for a hot gas path component is disclosed. The cooling system may include a component layer and a cover layer. The component layer may include a first inner surface and a second outer surface. The second outer surface may define a plurality of channels. The component layer may further define a plurality of passages extending generally between the first inner surface and the second outer surface. Each of the plurality of channels may be fluidly connected to at least one of the plurality of passages. The cover layer may be situated adjacent the second outer surface of the component layer. The plurality of passages may be configured to flow a cooling medium to the plurality of channels and provide impingement cooling to the cover layer. The plurality of channels may be configured to flow cooling medium therethrough, cooling the cover layer.
摘要翻译：公开了一种用于热气路径部件的冷却系统。冷却系统可以包括组件层和覆盖层。组件层可以包括第一内表面和第二外表面。第二外表面可以限定多个通道。组件层可以进一步限定大体上在第一内表面和第二外表面之间延伸的多个通道。多个通道中的每一个可以流体地连接到多个通道中的至少一个。覆盖层可以位于邻近部件层的第二外表面处。多个通道可以被配置成将冷却介质流动到多个通道并且向覆盖层提供冲击冷却。多个通道可以被配置成流过冷却介质，冷却覆盖层。

68. 发明申请

US20140027102A1 AIR-COOLED ENGINE SURFACE COOLER 有权
标题翻译：空气冷却发动机表面冷却器
公开(公告)号：US20140027102A1
公开(公告)日：2014-01-30
申请号：US13560779
申请日：2012-07-27
申请人： William Joseph ANTEL, JR. , Carlos Enrique DIAZ , Jorge Carretero BENIGNOS
发明人： William Joseph ANTEL, JR. , Carlos Enrique DIAZ , Jorge Carretero BENIGNOS
IPC分类号： F28F3/02 , B23P15/26
CPC分类号： F28F3/04 , B23P15/26 , F02C3/04 , F02C7/18 , F02K3/115 , F05D2220/323 , F05D2260/213 , F05D2260/2212 , F05D2260/22141 , F28D1/0246 , F28D1/06 , F28F1/16 , F28F3/02 , F28F3/048 , F28F3/12 , F28F13/003 , F28F13/12 , F28F21/084 , F28F2215/04 , Y02T50/671 , Y02T50/676 , Y10T29/4935
摘要： A surface cooler comprises a plate-like layer and a plurality of spaced-apart fins extending substantially perpendicular from an uppermost layer of the plate-like layer. The plurality of fins defining a plurality of air flow paths. The plurality of spaced-apart fins are configured to augment heat transfer of the surface cooler by increasing the turbulence levels of a fluid flowing through the airflow paths by promoting increased mixing with a resulting increase in the heat transfer coefficient of the surface cooler. A method of forming the surface cooler and an engine including the surface cooler.
摘要翻译：表面冷却器包括板状层和从板状层的最上层基本上垂直延伸的多个间隔开的散热片。多个翅片限定多个气流路径。多个间隔开的翅片构造成通过增加流过气流路径的流体的湍流水平来增加表面冷却器的热传递，从而通过促进增加的混合，从而导致表面冷却器的传热系数的增加。一种形成表面冷却器的方法和包括表面冷却器的发动机。

69. 发明申请

US20130343872A1 COOLED COMPONENT FOR THE TURBINE OF A GAS TURBINE ENGINE 有权
标题翻译：用于涡轮发动机涡轮机的冷却组件
公开(公告)号：US20130343872A1
公开(公告)日：2013-12-26
申请号：US13359180
申请日：2012-01-26
申请人： IAN TIBBOTT , DOUGAL R. JACKSON
发明人： IAN TIBBOTT , DOUGAL R. JACKSON
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , F01D5/186 , F01D5/187 , F01D5/188 , F01D5/20 , F01D9/06 , F01D9/065 , F05D2240/127 , F05D2240/81 , F05D2260/2212 , F05D2260/22141
摘要： A component for the turbine of a gas turbine engine is provided. The component two facing walls interconnected by one or more generally elongate divider members to partially define side-by-side, generally elongate, cooling fluid passage portions which form a multi-pass cooling passage within the component. The passage portions are connected in series fluid flow relationship by respective bends formed by joined ends of neighbouring of the passage portions. The component further includes one or more core tie linking passages formed in the divider members. One or more differential pressure reducing arrangements are formed in the multi-pass cooling passage adjacent respective of the core tie linking passages.
摘要翻译：提供了一种用于燃气涡轮发动机的涡轮机的部件。由两个面向对面的部件组成的壁由一个或多个大致细长的分隔件相互连接，以部分地限定并排大致细长的冷却流体通道部分，该部分形成多个部件内的多通道冷却通道。通道部分通过由相邻通道部分的连接端形成的相应的弯曲部以串联的流体流动关系连接。该部件还包括形成在分隔件中的一个或多个芯连接连接通道。在多通道冷却通道中形成有一个或多个差压减压装置，该多通道冷却通道与相互连接的芯连接通道相邻。

70. 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。

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