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1.发明申请TURBINE BLADE AIRFOILS INCLUDING FILM COOLING SYSTEMS, AND METHODS FOR FORMING AN IMPROVED FILM COOLED AIRFOIL OF A TURBINE BLADE 有权包括薄膜冷却系统的涡轮机叶片，以及用于形成涡轮叶片改进的薄膜冷却气流的方法公开(公告)号：US20140356188A1
公开(公告)日：2014-12-04
申请号：US13871655
申请日：2013-04-26
发明人： Vighneswara Rao Kollati , Balamurugan Srinivasan , Jong Liu , Daniel C. Crites , Luis Tapia , Malak Fouad Malak , Rajiv Rana
CPC分类号： F01D5/186 , B23P15/02 , F05D2230/10 , F05D2240/303 , F05D2240/305 , F05D2240/306 , Y02T50/676 , Y10T29/49341
摘要： Turbine blade airfoils, film cooling systems thereof, and methods for forming improved film cooled components are provided. The turbine blade airfoil has an external wall surface and comprises leading and trailing edges, pressure and suction sidewalls both extending between the leading and the trailing edges, an internal cavity, one or more isolation trenches in the external wall surface, a plurality of film cooling holes arranged in cooling rows, and a plurality of span-wise surface connectors interconnecting the outlets of the film cooling holes in the same cooling row to form a plurality of rows of interconnected film cooling holes. Each film cooling hole has an inlet connected to the internal cavity and an outlet opening onto the external wall surface. The span-wise surface connectors in at least one selected row of interconnected film cooling holes are disposed in the one or more isolation trenches.
摘要翻译： 提供了涡轮叶片翼型件，其薄膜冷却系统以及用于形成改进的薄膜冷却部件的方法。 涡轮叶片翼型件具有外壁表面并且包括前缘和后缘，压力和吸力侧壁均在前缘和后缘之间延伸，内腔，外壁表面中的一个或多个隔离沟槽，多个膜冷却 布置在冷却排中的孔，以及将相同冷却排中的膜冷却孔的出口互连的多个跨距表面连接器，以形成多排相互连接的膜冷却孔。 每个薄膜冷却孔具有连接到内部空腔的入口和外壁表面上的出口。 在至少一个所选择的互连薄膜冷却孔排中的跨度表面连接器设置在所述一个或多个隔离沟槽中。
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2.发明申请TURBINE BLADE AIRFOILS INCLUDING SHOWERHEAD FILM COOLING SYSTEMS, AND METHODS FOR FORMING AN IMPROVED SHOWERHEAD FILM COOLED AIRFOIL OF A TURBINE BLADE 有权涡轮叶片飞行器，包括淋浴膜冷却系统，以及形成改进的淋浴罩冷却涡轮机叶片的方法公开(公告)号：US20140154096A1
公开(公告)日：2014-06-05
申请号：US13692353
申请日：2012-12-03
发明人： Vighneswara Rao Kollati , Balamurugan Srinivasan , Jong Liu , Daniel Cregg Crites , Luis Tapia , Malak Fouad Malak , Rajiv Rana
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/187 , F05D2260/202 , Y02T50/676 , Y10T29/49341
摘要： Turbine blade airfoils, showerhead film cooling systems thereof, and methods for cooling the turbine blade airfoils using the same are provided. The airfoil has a leading edge and a trailing edge, a pressure sidewall and a suction sidewall both extending between the leading and the trailing edges, and an internal cavity for supplying cooling air. A showerhead of film cooling holes is connected to the internal cavity. Each film cooling hole has an inlet connected to the internal cavity and an outlet opening onto an external wall surface at the leading edge of the airfoil. A plurality of surface connectors is formed in the external wall surface. Each surface connector of the plurality of surface connectors interconnects the outlets of at least one selected pair of the film cooling holes.
摘要翻译： 提供了涡轮叶片翼型件，喷淋头膜冷却系统以及使用其的用于冷却涡轮叶片翼型件的方法。 翼型件具有在前缘和后缘之间延伸的前缘和后缘，压力侧壁和吸力侧壁，以及用于供应冷却空气的内部空腔。 薄膜冷却孔的喷头连接到内部空腔。 每个膜冷却孔具有连接到内部空腔的入口和在翼型的前缘处的外壁表面上的出口。 多个表面连接器形成在外壁表面中。 多个表面连接器中的每个表面连接器互连至少一个选定的一对薄膜冷却孔的出口。
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3.发明授权Turbine blade airfoils including showerhead film cooling systems, and methods for forming an improved showerhead film cooled airfoil of a turbine blade 有权涡轮叶片翼型件，包括喷头膜冷却系统，以及用于形成涡轮机叶片的改进的喷头薄膜冷却翼型的方法公开(公告)号：US09228440B2
公开(公告)日：2016-01-05
申请号：US13692353
申请日：2012-12-03
发明人： Vighneswara Rao Kollati , Balamurugan Srinivasan , Jong Liu , Daniel Cregg Crites , Luis Tapia , Malak Fouad Malak , Rajiv Rana
CPC分类号： F01D5/186 , F01D5/187 , F05D2260/202 , Y02T50/676 , Y10T29/49341
摘要： Turbine blade airfoils, showerhead film cooling systems thereof, and methods for cooling the turbine blade airfoils using the same are provided. The airfoil has a leading edge and a trailing edge, a pressure sidewall and a suction sidewall both extending between the leading and the trailing edges, and an internal cavity for supplying cooling air. A showerhead of film cooling holes is connected to the internal cavity. Each film cooling hole has an inlet connected to the internal cavity and an outlet opening onto an external wall surface at the leading edge of the airfoil. A plurality of surface connectors is formed in the external wall surface. Each surface connector of the plurality of surface connectors interconnects the outlets of at least one selected pair of the film cooling holes.
摘要翻译： 提供了涡轮叶片翼型件，喷淋头膜冷却系统以及使用其的用于冷却涡轮叶片翼型件的方法。 翼型件具有在前缘和后缘之间延伸的前缘和后缘，压力侧壁和吸力侧壁，以及用于供应冷却空气的内部空腔。 薄膜冷却孔的喷头连接到内部空腔。 每个膜冷却孔具有连接到内部空腔的入口和在翼型的前缘处的外壁表面上的出口。 多个表面连接器形成在外壁表面中。 多个表面连接器中的每个表面连接器互连至少一个选定的一对薄膜冷却孔的出口。
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公开(公告)号：US20150275763A1
公开(公告)日：2015-10-01
申请号：US14227924
申请日：2014-03-27
发明人： Shezan Kanjiyani , John Gintert , Rajiv Rana , Lorenzo Crosatti , Bradley Reed Tucker , Ed Zurmehly
CPC分类号： F02C7/18 , F01D5/187 , F01D11/08 , F01D25/12 , F01D25/14 , F02C3/10 , F05D2240/81 , F05D2260/201 , F05D2260/205 , Y02T50/673 , Y02T50/676
摘要： A turbine section includes a stator assembly having an inner diameter end wall, an outer diameter end wall, and a stator vane; a turbine rotor assembly including a rotor blade extending into the mainstream gas flow path; a housing including an annular shroud that circumscribes the rotor blade and at least partially defines the mainstream hot gas flow path; a first baffle arranged to define a first cavity with the outer diameter end wall of the stator assembly; a second baffle; and a third baffle arranged to define a second cavity with the second baffle and a third cavity with the shroud. The first cavity is fluidly coupled to the second cavity and the second cavity is fluidly coupled to the third cavity such that cooling air flows from the first cavity to the second cavity and from the second cavity to the third cavity.
摘要翻译： 涡轮部分包括具有内径端壁，外径端壁和定子叶片的定子组件; 涡轮转子组件，其包括延伸到主流气流路径中的转子叶片; 壳体，其包括环绕所述转子叶片并且至少部分地限定所述主流热气体流动路径的环形护罩; 第一挡板，布置成限定具有定子组件的外径端壁的第一腔; 第二挡板 以及第三挡板，其布置成限定具有第二挡板的第二空腔和具有护罩的第三空腔。 第一腔体流体地联接到第二腔体，而第二腔室流体耦合到第三空腔，使得冷却空气从第一空腔流到第二空腔，并从第二腔体流到第三空腔。
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公开(公告)号：US20140321965A1
公开(公告)日：2014-10-30
申请号：US13869085
申请日：2013-04-24
发明人： Rajiv Rana , Ardeshir Riahi , Bradley Reed Tucker , David Chou
IPC分类号： F01D9/02
CPC分类号： F01D9/065 , F01D5/187 , F05D2260/201 , F05D2260/202 , Y02T50/676
摘要： A turbine nozzle assembly includes an inner circumferential support platform, an outer circumferential support platform, and a plurality of airfoil vanes disposed between the inner circumferential support platform and the outer circumferential support platform. The turbine nozzle assembly further includes a plurality of impingement plates disposed along a radially outer surface of the outer circumferential support platform or a radially inner surface of the inner circumferential support platform, and a plurality of gap-maintaining features disposed between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates. Each gap-maintaining feature of the plurality of gap-maintaining features is provided at a height such that a cooling air flow space is maintained between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates.
摘要翻译： 涡轮喷嘴组件包括内周支撑平台，外周支撑平台以及设置在内圆周支撑平台和外圆周支撑平台之间的多个翼型叶片。 涡轮喷嘴组件还包括沿着外周支撑平台的径向外表面或内周支撑平台的径向内表面设置的多个冲击板，以及多个间隙保持特征，其设置在多个外周或 内圆周支撑平台和多个冲击板。 多个间隙保持特征的每个间隙保持特征都设置在使多个外周或内周支撑平台与多个冲击板之间保持冷却空气流动空间的高度。
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公开(公告)号：US09719362B2
公开(公告)日：2017-08-01
申请号：US13869085
申请日：2013-04-24
发明人： Rajiv Rana , Ardeshir Riahi , Bradley Reed Tucker , David Chou
CPC分类号： F01D9/065 , F01D5/187 , F05D2260/201 , F05D2260/202 , Y02T50/676
摘要： A turbine nozzle assembly includes an inner circumferential support platform, an outer circumferential support platform, and a plurality of airfoil vanes disposed between the inner circumferential support platform and the outer circumferential support platform. The turbine nozzle assembly further includes a plurality of impingement plates disposed along a radially outer surface of the outer circumferential support platform or a radially inner surface of the inner circumferential support platform, and a plurality of gap-maintaining features disposed between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates. Each gap-maintaining feature of the plurality of gap-maintaining features is provided at a height such that a cooling air flow space is maintained between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates.
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公开(公告)号：US09657642B2
公开(公告)日：2017-05-23
申请号：US14227924
申请日：2014-03-27
发明人： Shezan Kanjiyani , John Gintert , Rajiv Rana , Lorenzo Crosatti , Bradley Reed Tucker , Ed Zurmehly
CPC分类号： F02C7/18 , F01D5/187 , F01D11/08 , F01D25/12 , F01D25/14 , F02C3/10 , F05D2240/81 , F05D2260/201 , F05D2260/205 , Y02T50/673 , Y02T50/676
摘要： A turbine section includes a stator assembly having an inner diameter end wall, an outer diameter end wall, and a stator vane; a turbine rotor assembly including a rotor blade extending into the mainstream gas flow path; a housing including an annular shroud that circumscribes the rotor blade and at least partially defines the mainstream hot gas flow path; a first baffle arranged to define a first cavity with the outer diameter end wall of the stator assembly; a second baffle; and a third baffle arranged to define a second cavity with the second baffle and a third cavity with the shroud. The first cavity is fluidly coupled to the second cavity and the second cavity is fluidly coupled to the third cavity such that cooling air flows from the first cavity to the second cavity and from the second cavity to the third cavity.
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8.发明授权Turbine blade airfoils including film cooling systems, and methods for forming an improved film cooled airfoil of a turbine blade 有权包括膜冷却系统的涡轮叶片翼型以及用于形成涡轮叶片的改进的薄膜冷却翼型的方法公开(公告)号：US09562437B2
公开(公告)日：2017-02-07
申请号：US13871655
申请日：2013-04-26
发明人： Vighneswara Rao Kollati , Balamurugan Srinivasan , Jong Liu , Daniel C. Crites , Luis Tapia , Malak Fouad Malak , Rajiv Rana
CPC分类号： F01D5/186 , B23P15/02 , F05D2230/10 , F05D2240/303 , F05D2240/305 , F05D2240/306 , Y02T50/676 , Y10T29/49341
摘要： Turbine blade airfoils, film cooling systems thereof, and methods for forming improved film cooled components are provided. The turbine blade airfoil has an external wall surface and comprises leading and trailing edges, pressure and suction sidewalls both extending between the leading and the trailing edges, an internal cavity, one or more isolation trenches in the external wall surface, a plurality of film cooling holes arranged in cooling rows, and a plurality of span-wise surface connectors interconnecting the outlets of the film cooling holes in the same cooling row to form a plurality of rows of interconnected film cooling holes. Each film cooling hole has an inlet connected to the internal cavity and an outlet opening onto the external wall surface. The span-wise surface connectors in at least one selected row of interconnected film cooling holes are disposed in the one or more isolation trenches.
摘要翻译： 提供了涡轮叶片翼型件，其薄膜冷却系统以及用于形成改进的薄膜冷却部件的方法。 涡轮叶片翼型件具有外壁表面并且包括前缘和后缘，压力和吸力侧壁均在前缘和后缘之间延伸，内腔，外壁表面中的一个或多个隔离沟槽，多个膜冷却 布置在冷却排中的孔，以及将相同冷却排中的膜冷却孔的出口互连的多个跨距表面连接器，以形成多排相互连接的膜冷却孔。 每个薄膜冷却孔具有连接到内部空腔的入口和外壁表面上的出口。 在至少一个所选择的互连薄膜冷却孔排中的跨度表面连接器设置在所述一个或多个隔离沟槽中。
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