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1. 发明授权

US06558114B1 Gas turbine with baffle reducing hot gas ingress into interstage disc cavity 有权
标题翻译：带挡板的燃气轮机减少热气进入舱间盘腔
公开(公告)号：US06558114B1
公开(公告)日：2003-05-06
申请号：US09676061
申请日：2000-09-29
申请人： Joseph Theodore Tapley , John Y. Xia , Zhenhua Xiao
发明人： Joseph Theodore Tapley , John Y. Xia , Zhenhua Xiao
IPC分类号： F01D1104
CPC分类号： F01D11/001 , F01D5/081
摘要： The subcavity between a stator seal assembly and the upstream rotor disc in the interstage disc cavity of a gas turbine is divided into a radially inward region and a radially outward region by an annular baffle that extends from the seal assembly partially across the subcavity toward the rotor disc. The volume of cooling air injected into the interstage disc cavity can be reduced to increase turbine efficiency because the baffle interrupts recirculation in the subcavity to confine ingress of the hot main gas flow to the radially outward region away from the rotor seals.
摘要翻译：定子密封组件和燃气轮机的级间盘腔中的上游转子盘之间的子腔通过环形挡板分成径向向内的区域和径向向外的区域，该环形挡板从密封组件部分穿过子腔向转子光盘。可以减少注入到级间盘腔中的冷却空气的体积，以增加涡轮机的效率，因为挡板中断了子腔中的再循环，从而限制热的主气流进入远离转子密封件的径向向外的区域。

2. 发明授权

US06830432B1 Cooling of combustion turbine airfoil fillets 有权
标题翻译：燃油涡轮机翼型鱼片的冷却
公开(公告)号：US06830432B1
公开(公告)日：2004-12-14
申请号：US10603036
申请日：2003-06-24
申请人： Robert Kenmer Scott , Joseph Theodore Tapley
发明人： Robert Kenmer Scott , Joseph Theodore Tapley
IPC分类号： F01D518
CPC分类号： F01D5/186 , F01D5/145 , F05D2240/81 , F05D2260/202 , F05D2260/2214 , F05D2270/17
摘要： A turbine fluid guide member (10) including an airfoil portion (12), a platform portion (14) and fillet (16) joining the airfoil portion to the platform portion. Fillet cooling holes (18a-18f) are positioned in the turbine fluid guide member relative to a pressure side vortex flow (22) so that a cooling fluid flow (20) exiting the hole is directed to form a cooling film (32) over the fillet. The cooling holes may be positioned in the airfoil portion, the platform portion, or any combination thereof, depending on the geometry of the airfoil and resultant vortex flows around the airfoil. A method of cooling a fillet of the turbine fluid guide member may include identifying a vortex flow around the fillet and selectively positioning a hole relative to the vortex flow such that a cooling fluid flow exiting the hole is directed to form a cooling film over the fillet.
摘要翻译：一种涡轮流体引导构件（10），包括翼型部分（12），平台部分（14）和将翼型部分连接到平台部分的圆角（16）。圆角冷却孔（18a-18f）相对于压力侧涡流（22）定位在涡轮流体引导构件中，使得离开孔的冷却流体流（20）被引导以形成冷却膜鱼片。取决于翼型件的几何结构和围绕翼型的合成的涡流，冷却孔可以定位在翼型部分，平台部分或其任何组合中。冷却涡轮流体引导构件的圆角的方法可以包括识别围绕圆角的涡流，并且相对于涡流选择性地定位孔，使得离开孔的冷却流体流被引导以在圆角上形成冷却膜。

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