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1. 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％。

2. 发明申请

US20110103932A1 STATOR BLADE FOR A GAS TURBINE AND GAS TURBINE HAVING SAME 有权
标题翻译：用于气体涡轮和气体涡轮的定子叶片
公开(公告)号：US20110103932A1
公开(公告)日：2011-05-05
申请号：US12892423
申请日：2010-09-28
申请人： Roland DUECKERSHOFF , Shailendra NAIK , Martin SCHNIEDER
发明人： Roland DUECKERSHOFF , Shailendra NAIK , Martin SCHNIEDER
IPC分类号： F01D9/02
CPC分类号： F01D5/187 , F01D9/041 , F05D2220/3215 , F05D2250/185 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
摘要： A stator blade for a gas turbine with sequential combustion, has a blade airfoil which extends in the radial direction between a blade tip and a shroud, with cooling passages extending inside the blade airfoil, through which a cooling medium can flow for cooling the blade and can then discharge from the stator blade into the hot gas flow flowing through the turbine. The blade airfoil has a sharply curved shape in space in the radial direction, and three cooling passages, which extend in the radial direction, arranged inside the blade airfoil in series in the hot gas flow direction and are interconnected by deflection regions, which are arranged at ends of the blade airfoil, so that the cooling medium flows through the cooling passages one after the other, with change of direction. The cooling passages follow the curvature of the blade airfoil in space in the radial direction.
摘要翻译：一种用于具有顺序燃烧的燃气轮机的定子叶片具有在叶片尖端和护罩之间沿径向方向延伸的叶片翼型件，其中在叶片翼型内部延伸有冷却通道，冷却介质可通过该叶片气流流动以冷却叶片，然后可以从定子叶片排出流入流经涡轮的热气流。叶片翼型件在径向空间中具有急剧弯曲的形状，并且在径向方向上延伸的三个冷却通道在热气流方向上串联布置在叶片翼型内部并且通过偏转区域相互连接，偏转区域被布置在叶片翼型的端部处，使得冷却介质随着方向的改变一个接一个地流过冷却通道。冷却通道在径向方向上沿着空间中的叶片翼型的曲率。

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