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1. 发明授权

US08444375B2 Cooled blade for a gas turbine, method for producing such a blade, and gas turbine having such a blade 有权
标题翻译：用于燃气轮机的冷却叶片，用于生产这种叶片的方法，以及具有这种叶片的燃气轮机
公开(公告)号：US08444375B2
公开(公告)日：2013-05-21
申请号：US13095427
申请日：2011-04-27
申请人： Shailendra Naik , Gaurav Pathak
发明人： Shailendra Naik , Gaurav Pathak
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/81 , F05D2250/292 , F05D2260/2212 , F05D2260/607 , Y10T29/49341
摘要： A blade for a gas turbine includes an airfoil extending in radial direction of the turbine or longitudinal direction of the blade, respectively, between a platform and a blade tip. The airfoil is bordered across the airfoil by a leading edge and a trailing edge and has a suction side and a pressure side. At the trailing edge a first cooling passage runs parallel to the trailing edge from the platform to the blade tip in the interior of the airfoil. The cooling passage is supplied with a cooling air flow from the platform side, and from which cooling air is discharged through a plurality of cooling holes arranged all over the blade. For such a blade the cooling is optimized by providing a first cooling passage, the passage area of which is tapered in radial direction by between 35% and 59%.
摘要翻译：用于燃气轮机的叶片包括在平台和叶片尖端之间分别在涡轮的径向方向或叶片的纵向方向上延伸的翼型件。机翼通过前缘和后缘横跨翼型，并且具有吸力侧和压力侧。在后缘处，第一冷却通道平行于后缘从平台延伸到叶片内部的叶片尖端。向冷却通道供给来自平台侧的冷却空气流，通过布置在整个叶片上的多个冷却孔从其排出冷却空气。对于这样的叶片，通过提供第一冷却通道来优化冷却，其通道面积在径向方向上逐渐变细35％至59％。

2. 发明申请

US20120070308A1 COOLED BLADE FOR A GAS TURBINE 审中-公开
标题翻译：用于气体涡轮的冷却叶片
公开(公告)号：US20120070308A1
公开(公告)日：2012-03-22
申请号：US13234592
申请日：2011-09-16
申请人： Shailendra Naik , Gaurav Pathak
发明人： Shailendra Naik , Gaurav Pathak
IPC分类号： F01D5/18
CPC分类号： F01D5/20 , F05D2240/307 , F05D2250/231 , F05D2250/232 , F05D2260/20 , F05D2260/202
摘要： A cooled blade for a gas turbine includes an airfoil section which extends in the radial direction of the turbine or in the longitudinal direction of the blade between a platform and a blade tip which is provided with a cap. The airfoil section is bounded transversely with respect to the longitudinal direction by a leading edge and a trailing edge and has a pressure face and a suction face. Cooling channels extend in a radial direction between the platform and the blade tip in an interior of the airfoil section. The cooling channels can be acted upon by a cooling air flow from the platform. The blade tip is cooled by first cooling holes for convection cooling provided on the pressure face of the blade, and second cooling holes for film cooling provided on the suction side of the blade, through the cap of the blade, in the blade tip from the cooling channels, and distributed over the blade width.
摘要翻译：用于燃气轮机的冷却叶片包括翼型部分，其在涡轮机的径向方向上或在叶片的纵向方向上在平台和设置有盖的叶片尖端之间延伸。翼型部分通过前缘和后缘相对于纵向方向横向限定，并具有压力面和吸力面。冷却通道在翼型部分的内部中在平台和叶片尖端之间的径向方向上延伸。冷却通道可以通过来自平台的冷却空气流动。叶片尖端由设置在叶片的压力面上的用于对流冷却的第一冷却孔冷却，并且在叶片的吸入侧通过叶片的盖在叶片尖端从第二冷却孔冷却通道，并分布在刀片宽度上。

3. 发明申请

US20110243755A1 COOLED BLADE FOR A GAS TURBINE, METHOD FOR PRODUCING SUCH A BLADE, AND GAS TURBINE HAVING SUCH A BLADE 有权
标题翻译：用于气体涡轮的冷却叶片，用于生产这种叶片的方法和具有这种叶片的气体涡轮机
公开(公告)号：US20110243755A1
公开(公告)日：2011-10-06
申请号：US13095427
申请日：2011-04-27
申请人： Shailendra NAIK , Gaurav Pathak
发明人： Shailendra NAIK , Gaurav Pathak
IPC分类号： F01D5/18 , B23P15/02
CPC分类号： F01D5/187 , F05D2240/81 , F05D2250/292 , F05D2260/2212 , F05D2260/607 , Y10T29/49341
摘要： A blade for a gas turbine includes an airfoil extending in radial direction of the turbine or longitudinal direction of the blade, respectively, between a platform and a blade tip. The airfoil is bordered across the airfoil by a leading edge and a trailing edge and has a suction side and a pressure side. At the trailing edge a first cooling passage runs parallel to the trailing edge from the platform to the blade tip in the interior of the airfoil. The cooling passage is supplied with a cooling air flow from the platform side, and from which cooling air is discharged through a plurality of cooling holes arranged all over the blade. For such a blade the cooling is optimized by providing a first cooling passage, the passage area of which is tapered in radial direction by between 35% and 59%.
摘要翻译：用于燃气轮机的叶片包括在平台和叶片尖端之间分别在涡轮的径向方向或叶片的纵向方向上延伸的翼型件。机翼通过前缘和后缘横跨翼型，并且具有吸力侧和压力侧。在后缘处，第一冷却通道平行于后缘从平台延伸到叶片内部的叶片尖端。向冷却通道供给来自平台侧的冷却空气流，通过布置在整个叶片上的多个冷却孔从其排出冷却空气。对于这样的叶片，通过提供第一冷却通道来优化冷却，其通道面积在径向方向上逐渐变细35％至59％。

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