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1.发明授权Turbine airfoil concave cooling passage using dual-swirl flow mechanism and method 有权涡轮翼型凹形冷却通道采用双旋流动机构及方法公开(公告)号：US08376706B2
公开(公告)日：2013-02-19
申请号：US11863744
申请日：2007-09-28
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/121 , F05D2240/303 , F05D2250/314 , F05D2250/33 , F05D2250/70 , F05D2260/205 , F05D2260/2212 , F05D2260/22141 , F05D2260/2322
摘要： A turbine airfoil includes a leading edge having a concave cooling flow passage. An apex of the concave cooling flow passage divides the flow passage into adjacent regions. The turbine airfoil includes a first plurality of turbulators disposed in one of the adjacent regions, and a second plurality of turbulators disposed in the other of the adjacent regions. The first and second pluralities of turbulators are positioned relative to one another to divert cooling flow in opposing swirl streams that recombine along the apex and to effect a desired heat transfer and pressure loss.
摘要翻译： 涡轮机翼片包括具有凹形冷却流道的前缘。 凹形冷却流道的顶点将流动通道分成相邻的区域。 涡轮机翼片包括设置在相邻区域之一中的第一多个湍流器和设置在相邻区域中的另一个中的第二多个湍流器。 第一和第二多个紊流器相对于彼此定位，以使沿着顶点重新组合的相反旋流中的冷却流转向并实现所需的传热和压力损失。
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公开(公告)号：US20110259017A1
公开(公告)日：2011-10-27
申请号：US12765372
申请日：2010-04-22
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。
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公开(公告)号：US08651805B2
公开(公告)日：2014-02-18
申请号：US12765372
申请日：2010-04-22
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。
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4.发明申请Turbine Airfoil Concave Cooling Passage Using Dual-Swirl Flow Mechanism and Method 有权涡轮机翼冷却通道采用双旋流动机理和方法公开(公告)号：US20090087312A1
公开(公告)日：2009-04-02
申请号：US11863744
申请日：2007-09-28
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/121 , F05D2240/303 , F05D2250/314 , F05D2250/33 , F05D2250/70 , F05D2260/205 , F05D2260/2212 , F05D2260/22141 , F05D2260/2322
摘要： A turbine airfoil includes a leading edge having a concave cooling flow passage. An apex of the concave cooling flow passage divides the flow passage into adjacent regions. The turbine airfoil includes a first plurality of turbulators disposed in one of the adjacent regions, and a second plurality of turbulators disposed in the other of the adjacent regions. The first and second pluralities of turbulators are positioned relative to one another to divert cooling flow in opposing swirl streams that recombine along the apex and to effect a desired heat transfer and pressure loss.
摘要翻译： 涡轮机翼片包括具有凹形冷却流道的前缘。 凹形冷却流道的顶点将流动通道分成相邻的区域。 涡轮机翼片包括设置在相邻区域之一中的第一多个湍流器和设置在相邻区域中的另一个中的第二多个湍流器。 第一和第二多个紊流器相对于彼此定位，以使沿着顶点重新组合的相反旋流中的冷却流转向并实现所需的传热和压力损失。
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公开(公告)号：US09376931B2
公开(公告)日：2016-06-28
申请号：US13359962
申请日：2012-01-27
CPC分类号： F01D25/002 , F04D29/5846 , F05D2210/13 , F05D2260/2322 , F05D2260/607
摘要： A turbomachine passage cleaning system includes a first airflow passage having a first inlet configured and disposed to fluidly connect to a compressor portion, a first outlet configured and disposed to fluidly connect to a turbine portion, and a first intermediate portion including a first strainer. A second airflow passage is fluidly coupled to the first airflow passage. The second airflow passage has a second intermediate portion having second strainer. A first valve is arranged in the first intermediate portion upstream from the first strainer, and a second valve is arranged in the second intermediate portion upstream from the second strainer. The first and second valves are selectively operated to control fluid flow into respective ones of the first and second airflow passages to filter air passing from a turbomachine compressor portion to a turbomachine turbine portion.
摘要翻译： 涡轮机通道清洁系统包括第一气流通道，其具有构造和设置成流体连接到压缩机部分的第一入口，被配置和设置成流体连接到涡轮机部分的第一出口和包括第一过滤器的第一中间部分。 第二气流通道流体地联接到第一气流通道。 第二气流通道具有具有第二过滤器的第二中间部分。 第一阀布置在第一过滤器上游的第一中间部分中，并且第二阀布置在第二过滤器上游的第二中间部分中。 选择性地操作第一阀和第二阀以控制流入第一和第二气流通道中的相应流体的流体，以过滤从涡轮机压缩机部分流到涡轮机涡轮机部分的空气。
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公开(公告)号：US09175565B2
公开(公告)日：2015-11-03
申请号：US13566189
申请日：2012-08-03
CPC分类号： F01D5/081 , F01D11/001 , F01D11/04 , F05D2240/55 , F05D2240/81 , Y02T50/673 , Y02T50/676
摘要： A seal in a turbine of a combustion turbine engine is described. The seal is formed within a trench cavity defined between a rotor blade and a stator blade. The stator blade includes a sidewall projection and the rotor blade includes an angel wing projection extending toward the stator blade. The side wall projection overhangs the angel wing projection. The seal include: a port disposed on an inboard surface of the stator projection; and deflecting structure disposed on the angel wing projection. The deflecting structure may be configured to receive the fluid expelled from the port and deflect the fluid toward an inlet of the trench cavity.
摘要翻译： 描述了燃气涡轮发动机的涡轮机中的密封件。 密封件形成在限定在转子叶片和定子叶片之间的沟槽腔内。 定子叶片包括侧壁突起，转子叶片包括向定子叶片延伸的天使翼突起。 侧壁突起悬挂天使翼投影。 密封件包括：设置在定子突起的内表面上的端口; 以及设置在天使翼突起上的偏转结构。 偏转结构可以被配置为接收从端口排出的流体并使流体朝向沟槽腔的入口偏转。
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公开(公告)号：US08967957B2
公开(公告)日：2015-03-03
申请号：US13288100
申请日：2011-11-03
CPC分类号： F01D11/02 , F01D5/288 , Y02T50/671
摘要： A rotating airfoil component equipped with one or more angel wings that inhibit the ingress of a hot working fluid into interior regions of a turbomachine in which the component is installed. The component includes an airfoil and a feature for mounting the component to enable rotation of the component within the turbomachine. An angel wing projects from the component to have a first surface facing the airfoil, an oppositely-disposed second surface facing the mounting feature, and at least one lateral surface therebetween. A thermal-insulating coating system is present on the first surface to inhibit heat transfer from the working fluid to the angel wing but not on the second or lateral surfaces so as not to inhibit heat transfer from the second and lateral surfaces of the angel wing.
摘要翻译： 装备有一个或多个天使翼的旋转翼型零件，其阻止热工作流体进入其中安装该部件的涡轮机的内部区域。 该部件包括翼型件和用于安装部件以使部件在涡轮机内旋转的特征。 天使翼从部件突出以具有面向翼型的第一表面，面对安装特征的相对设置的第二表面以及其间的至少一个侧表面。 绝热涂层系统存在于第一表面上以抑制从工作流体传递到天使翼而不是在第二或侧面上的热传递，从而不会妨碍从天使翼的第二和侧面的热传递。
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公开(公告)号：US08915712B2
公开(公告)日：2014-12-23
申请号：US13164113
申请日：2011-06-20
申请人： Gary Michael Itzel , Dipankar Pal
发明人： Gary Michael Itzel , Dipankar Pal
CPC分类号： F01D5/187 , F05D2240/81 , F05D2260/202 , F05D2260/22141
摘要： A hot gas path component is provided and includes a body having a surface and being formed to define a cavity, the cavity employing coolant flow through a pin-fin bank with coolant discharge through film-cooling holes defined on the surface, the pin-fin bank including first and second pluralities of pin-fins, the first plurality of pin-fins and the second plurality of pin-fins each being aligned with a determined flow streamline, and any two pin-fins of the first and second pluralities of pin-fins being separated from one another by a gap as a function of a film-cooling hole dimension.
摘要翻译： 提供了一种热气体通道部件，其包括具有表面并形成为限定空腔的本体，所述腔体采用冷却剂流过穿过翅片组的销翅片组，其中冷却剂通过限定在表面上的薄膜冷却孔排出， 其包括第一和第二多个销翅片，所述第一多个销翅片和所述第二多个销翅片各自与确定的流线路对准，并且所述第一和第二多个针脚翅片的任何两个销翅片， 翅片通过作为膜冷却孔尺寸的函数的间隙彼此分离。
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公开(公告)号：US08807944B2
公开(公告)日：2014-08-19
申请号：US12983400
申请日：2011-01-03
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , F01D5/183 , F05D2300/612 , Y02T50/672 , Y02T50/676
摘要： An airfoil component for use in a turbomachine, and method of promoting the heat transfer characteristics within the component. The component includes an airfoil portion having a span-wise direction delimited by an airfoil root and airfoil tip, and a chord-wise direction delimited by leading and trailing edges. A chamber within the airfoil portion contains a permeable foam member. The chamber is fluidically connected to a cooling fluid source and to a cooling hole through first and second passages, respectively, within the airfoil portion. The chamber is located relative to the first and second passages so as to be offset in the chord-wise direction therefrom so that cooling fluid entering the chamber through the first passage is diverted by the foam member in the chord-wise direction before exiting the airfoil portion through the cooling hole.
摘要翻译： 用于涡轮机械的翼型部件以及促进部件内的传热特性的方法。 该部件包括具有由翼型根部和翼型端部限定的跨度方向的翼型部分和由前缘和后缘限定的弦向。 翼型部分内的腔室包含渗透性泡沫构件。 腔室分别通过第一通道和第二通道流体地连接到冷却流体源，并且分别连接到翼型部分内的冷却孔。 腔室相对于第一和第二通道定位，以便沿着其顺时针方向偏移，使得在离开翼型之前通过第一通道进入腔室的冷却流体被沿着顺时针方向的泡沫构件转向 部分通过冷却孔。
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公开(公告)号：US08657574B2
公开(公告)日：2014-02-25
申请号：US12939576
申请日：2010-11-04
申请人： Sergio Daniel Marques Amaral , Gary Michael Itzel , Xiuzhang James Zhang , Camilo Andres Sampayo
发明人： Sergio Daniel Marques Amaral , Gary Michael Itzel , Xiuzhang James Zhang , Camilo Andres Sampayo
IPC分类号： F01D5/18
CPC分类号： F01D5/081 , F01D5/22 , F01D25/12 , F05D2240/57 , F05D2260/96
摘要： A turbine bucket includes an airfoil, a platform adjacent to the airfoil, and a shank adjacent to the platform. The shank defines a shank cavity, and a divider in the shank cavity creates a pressure differential across the shank cavity. A method for cooling a turbine bucket includes directing a fluid to a forward shank cavity and creating a pressure differential between the forward shank cavity and an aft shank cavity.
摘要翻译： 涡轮机桶包括翼型件，与翼型件相邻的平台以及与该平台相邻的柄部。 柄部限定了柄腔，并且柄腔中的分隔件在柄腔中形成压差。 一种用于冷却涡轮机铲斗的方法包括将流体引导到前柄腔，并在前柄腔和后柄腔之间产生压力差。
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