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公开(公告)号：US20140083116A1
公开(公告)日：2014-03-27
申请号：US13629284
申请日：2012-09-27
CPC分类号： F01D5/187 , F05D2260/201 , F05D2260/202 , F05D2260/221 , Y02T50/673 , Y02T50/676
摘要： A turbine rotor blade for a turbine section of an engine is provided. The rotor blade includes a platform and an airfoil extending from the platform into a mainstream gas path of the turbine section. The airfoil includes a pressure side wall, a suction side wall joined to the pressure side wall at a leading edge and a trailing edge, and a tip cap extending between the suction side wall and the pressure side wall. The rotor blade further includes an internal cooling circuit having a tip cap passage configured to deliver cooling air to the tip cap and a flow accelerator positioned within the tip cap passage of the internal cooling circuit.
摘要翻译： 提供了一种用于发动机的涡轮机部分的涡轮机转子叶片。 转子叶片包括平台和从平台延伸到涡轮部分的主流气体路径中的翼型件。 翼型件包括压力侧壁，在前缘和后缘处连接到压力侧壁的吸力侧壁和在吸力侧壁和压力侧壁之间延伸的尖端盖。 转子叶片还包括内部冷却回路，其具有构造成将冷却空气输送到顶盖的顶端通道和位于内部冷却回路的顶端通道内的流动加速器。
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2.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：US09546554B2
公开(公告)日：2017-01-17
申请号：US13629284
申请日：2012-09-27
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2260/201 , F05D2260/202 , F05D2260/221 , Y02T50/673 , Y02T50/676
摘要： A turbine rotor blade for a turbine section of an engine is provided. The rotor blade includes a platform and an airfoil extending from the platform into a mainstream gas path of the turbine section. The airfoil includes a pressure side wall, a suction side wall joined to the pressure side wall at a leading edge and a trailing edge, and a tip cap extending between the suction side wall and the pressure side wall. The rotor blade further includes an internal cooling circuit having a tip cap passage configured to deliver cooling air to the tip cap and a flow accelerator positioned within the tip cap passage of the internal cooling circuit.
摘要翻译： 提供了一种用于发动机的涡轮机部分的涡轮机转子叶片。 转子叶片包括平台和从平台延伸到涡轮部分的主流气体路径中的翼型件。 翼型件包括压力侧壁，在前缘和后缘处连接到压力侧壁的吸力侧壁和在吸力侧壁和压力侧壁之间延伸的尖端盖。 转子叶片还包括内部冷却回路，其具有构造成将冷却空气输送到顶盖的顶端通道和位于内部冷却回路的顶端通道内的流动加速器。
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公开(公告)号：US09394798B2
公开(公告)日：2016-07-19
申请号：US13855417
申请日：2013-04-02
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F05D2220/32 , F05D2240/121 , F05D2250/231 , F05D2250/232 , F05D2260/201 , Y02T50/671 , Y02T50/676
摘要： An airfoil for a gas turbine engine is provided. The airfoil includes a body with a leading edge, a trailing edge, a first side wall extending between the leading edge and the trailing edge, and a second side wall extending between the leading edge and the trailing edge. The body defines an interior cavity. The airfoil includes an interior wall disposed within the interior cavity of the body and extending between the first wall and the second wall to define a supply chamber and a leading edge chamber. The interior wall defines a cooling hole with a base portion and a locally extended portion to direct cooling air from the supply chamber to the leading edge chamber such that the cooling air impinges upon the leading edge.
摘要翻译： 提供了一种用于燃气涡轮发动机的翼型件。 翼型件包括具有前缘的主体，后缘，在前缘和后缘之间延伸的第一侧壁，以及在前缘和后缘之间延伸的第二侧壁。 身体定义一个内腔。 所述翼型件包括设置在所述主体的内部空腔内并在所述第一壁和所述第二壁之间延伸的内壁，以限定供应室和前缘室。 内壁限定具有基部和局部延伸部分的冷却孔，以将冷却空气从供应室引导到前缘室，使得冷却空气撞击前缘。
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公开(公告)号：US20150082808A1
公开(公告)日：2015-03-26
申请号：US13855417
申请日：2013-04-02
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F05D2220/32 , F05D2240/121 , F05D2250/231 , F05D2250/232 , F05D2260/201 , Y02T50/671 , Y02T50/676
摘要： An airfoil for a gas turbine engine is provided. The airfoil includes a body with a leading edge, a trailing edge, a first side wall extending between the leading edge and the trailing edge, and a second side wall extending between the leading edge and the trailing edge. The body defines an interior cavity. The airfoil includes an interior wall disposed within the interior cavity of the body and extending between the first wall and the second wall to define a supply chamber and a leading edge chamber. The interior wall defines a cooling hole with a base portion and a locally extended portion to direct cooling air from the supply chamber to the leading edge chamber such that the cooling air impinges upon the leading edge.
摘要翻译： 提供了一种用于燃气涡轮发动机的翼型件。 翼型件包括具有前缘的主体，后缘，在前缘和后缘之间延伸的第一侧壁，以及在前缘和后缘之间延伸的第二侧壁。 身体定义一个内腔。 所述翼型件包括设置在所述主体的内部空腔内并在所述第一壁和所述第二壁之间延伸的内壁，以限定供应室和前缘室。 内壁限定具有基部和局部延伸部分的冷却孔，以将冷却空气从供应室引导到前缘室，使得冷却空气撞击前缘。
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6.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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