公开(公告)号：US20110236223A1

公开(公告)日：2011-09-29

申请号：US13075234

申请日：2011-03-30

申请人： Christoph Nagler ,  Erich Kreiselmaier ,  Jose McFeat Anguisola ,  Sergei Riazantsev

发明人： Christoph Nagler ,  Erich Kreiselmaier ,  Jose McFeat Anguisola ,  Sergei Riazantsev

IPC分类号： F01D5/18

CPC分类号： F01D5/187 ,  F05D2240/80 ,  F05D2250/24 ,  Y02T50/676

摘要： A blade for a gas turbine includes an airfoil extending in a longitudinal direction and extending transversely to the longitudinal direction between a leading edge and a trailing edge. The airfoil has a pressure side, a suction side, and a slot-like cooling medium outlet extending along the trailing edge. The cooling medium outlet is configured to discharge cooling medium supplied from an inner space of the blade. A platform extends transversely to the longitudinal direction. An end of the airfoil merges into an underside of the platform and has a transition from the airfoil to the platform at the trailing edge of the airfoil that increases in thickness in a direction toward the underside of the platform. The cooling medium outlet extends into the platform so as to reduce an operating temperature in a region of the transition from the blade airfoil to the platform.

摘要翻译： 用于燃气轮机的叶片包括在纵向方向上延伸并且在前缘和后缘之间横向于纵向方向延伸的翼型件。 翼型件具有压力侧，吸力侧和沿着后缘延伸​​的槽状冷却介质出口。 冷却介质出口构造成排出从叶片的内部空间供给的冷却介质。 平台横向于纵向延伸。 翼型的一端合并到平台的下侧，并且在翼型的后缘处具有从翼型到平台的过渡，其在朝向平台的下侧的方向上增加厚度。 冷却介质出口延伸到平台中，以便在从叶片翼型到平台的过渡区域中降低工作温度。

公开(公告)号：US20110070089A1

公开(公告)日：2011-03-24

申请号：US12884851

申请日：2010-09-17

申请人： Erich Kreiselmaier ,  Jose Anguisola McFeat ,  Christoph Nagler ,  Sergei Riazantsev ,  Brian Kenneth Wardle

发明人： Erich Kreiselmaier ,  Jose Anguisola McFeat ,  Christoph Nagler ,  Sergei Riazantsev ,  Brian Kenneth Wardle

IPC分类号： F01D5/30

CPC分类号： F01D25/246 ,  F01D11/005 ,  F01D25/08 ,  F05D2240/10 ,  F05D2240/11 ,  F05D2240/81 ,  F05D2270/114

摘要： A stator blade for a gas turbine includes a blade airfoil extending in a longitudinal direction of the blade and is delimited by leading and trailing edges. The stator blade includes a shroud, whose inner side is exposed to hot gas which flows through the gas turbine. A hook-like fastening element for fastening the stator blade on a casing of the gas turbine projects outwards in the region of the trailing edge. The fastening element has a locating slot above the trailing edge for fixing a heat shield, which is connected to the shroud in the flow direction of the hot gas. A cavity is provided on the shroud between the locating slot for the heat shield and the trailing edge of the blade airfoil for reducing the thermal and mechanical stresses in the region of transition between the trailing edge and shroud, thereby extending the service life of the stator blade.

摘要翻译： 一种用于燃气轮机的定子叶片包括在叶片的纵向方向上延伸并由前缘和后缘限定的叶片翼型件。 定子叶片包括护罩，其内侧暴露于流过燃气轮机的热气体。 用于将定子叶片紧固在燃气涡轮机壳体上的钩状紧固元件在后缘区域中向外突出。 紧固元件具有在后缘上方的定位槽，用于固定热屏蔽件，该隔热罩沿着热气体的流动方向连接到护罩。 在护罩之间设置有用于隔热罩的定位槽和叶片翼型的后缘之间的空腔，用于减小后缘和护罩之间的过渡区域内的热和机械应力，从而延长了定子的使用寿命 刀。

公开(公告)号：US20110008177A1

公开(公告)日：2011-01-13

申请号：US12783046

申请日：2010-05-19

申请人： Jose ANGUISOLA MCFEAT ,  Erich Kreiselmaier ,  Christoph Nagler ,  Sergei Riazantsev

发明人： Jose ANGUISOLA MCFEAT ,  Erich Kreiselmaier ,  Christoph Nagler ,  Sergei Riazantsev

IPC分类号： F01D5/18

CPC分类号： F01D5/186 ,  F01D5/188 ,  F01D9/02 ,  F05D2240/81 ,  F05D2260/201

摘要： The disclosure relates to a hollow gas turbine vane that is cooled by an arrangement configured to sequential cooling an endwall of the vane and its airfoil and, at the same time, the two endwalls of the vane. This arrangement can reduce cooling air demand, which can have a positive effect on the turbines efficiency.

摘要翻译： 本发明涉及一种中空燃气涡轮机叶片，该中空燃气涡轮机叶片由构造成顺序冷却叶片的端壁及其翼型并且同时为叶片的两个端壁顺序冷却的装置而冷却。 这种布置可以减少冷却空气需求，这可能对涡轮机的效率产生积极的影响。