公开(公告)号：US07467924B2

公开(公告)日：2008-12-23

申请号：US11205274

申请日：2005-08-16

申请人： Robert A. Charbonneau ,  Kenneth P. Botticello ,  Shawn J. Gregg ,  Kirk David Hlavaty ,  Jeffrey R. Levine ,  Kenneth A. Lonczak ,  Craig R. McGarrah ,  Dominic J. Mongillo ,  Lisa P. O'Neill ,  Edward Pietraszkiewicz ,  Richard M. Salzillo ,  Heather Ann Terry

发明人： Robert A. Charbonneau ,  Kenneth P. Botticello ,  Shawn J. Gregg ,  Kirk David Hlavaty ,  Jeffrey R. Levine ,  Kenneth A. Lonczak ,  Craig R. McGarrah ,  Dominic J. Mongillo ,  Lisa P. O'Neill ,  Edward Pietraszkiewicz ,  Richard M. Salzillo ,  Heather Ann Terry

IPC分类号： F01D5/10

CPC分类号： F01D5/3007 ,  F01D5/22 ,  F05D2230/31 ,  F05D2300/132

摘要： The present invention provides a turbine blade having a revised under-platform structure including a unique coating combination that reduces mechanical stress factors within the turbine blade. The turbine blade includes a platform with an airfoil extending upwardly from the airfoil and a root portion extending downwardly from the platform. Two suction side tabs extend a first distance outward from a suction side of the root potion. Two pressure side tabs extend outward from a pressure side of the root portion. One of the two pressure side tabs extends outward a distance similar to the first distance, however, the other of the two pressure side tabs extends outward a distance much smaller than the first distance, which reduces stresses acting on the turbine blade. In addition, a plurality of coatings are systematically applied to the turbine blade to further reduce mechanical stress factors and improve cooling.

摘要翻译： 本发明提供一种涡轮叶片，其具有经修改的平台外结构，其包括独特的涂层组合，其减小涡轮叶片内的机械应力因素。 涡轮叶片包括具有从翼型件向上延伸的翼型件和从该平台向下延伸的根部的平台。 两个吸力侧翼片从根部的吸力侧向外延伸第一距离。 两个压力侧翼片从根部的压力侧向外延伸。 两个压力侧翼片之一向外延伸一段类似于第一距离的距离，然而，两个压力侧翼片中的另一个突出部向外延伸远远小于第一距离，这减小了作用在涡轮叶片上的应力。 另外，将多个涂层系统地施加到涡轮叶片上，以进一步减少机械应力因素并改善冷却。

公开(公告)号：US07452186B2

公开(公告)日：2008-11-18

申请号：US11205299

申请日：2005-08-16

申请人： Robert A. Charbonneau ,  Kenneth P. Botticello ,  Shawn J. Gregg ,  Kirk David Hlavaty ,  Jeffrey R. Levine ,  Kenneth A. Lonczak ,  Craig R. McGarrah ,  Dominic J. Mongillo ,  Lisa P. O'Neill ,  Edward Pietraszkiewicz ,  Richard M. Salzillo ,  Heather Ann Terry

发明人： Robert A. Charbonneau ,  Kenneth P. Botticello ,  Shawn J. Gregg ,  Kirk David Hlavaty ,  Jeffrey R. Levine ,  Kenneth A. Lonczak ,  Craig R. McGarrah ,  Dominic J. Mongillo ,  Lisa P. O'Neill ,  Edward Pietraszkiewicz ,  Richard M. Salzillo ,  Heather Ann Terry

IPC分类号： F01D5/18

CPC分类号： F01D5/187 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/676

摘要： The present invention provides an improved cooling circuit for a trailing edge of a turbine blade. The cooling circuit includes an inlet passage that receives a airflow and distributes the airflow through a feed passage. The feed passage primarily includes trip strips, at least one barrier including cross-over holes, teardrop shaped protrusions, and pockets disposed along a trailing edge. The geometry and positioning of both the cross-over holes and teardrop shaped protrusions downstream of the cross-over holes have been optimized to maximize cooling efficiency and reduce airflow. An improved transition between the inlet passage and the feed passage is also provided, which is arcuate and allows the airflow to maintain attachment and flow unimpeded from the inlet passage to the feed passage. The geometry of the pockets disposed along the trailing edge is optimized to improve cooling.

摘要翻译： 本发明提供了一种用于涡轮叶片的后缘的改进的冷却回路。 冷却回路包括入口通道，其接收气流并将气流分配通过进料通道。 进料通道主要包括跳闸带，至少一个屏障，包括交叉孔，泪珠形突起和沿后缘设置的凹穴。 交叉孔下游的交叉孔和泪滴形突起的几何形状和定位已被优化，以最大化冷却效率并减少气流。 还提供了入口通道和进料通道之间的改进的过渡，其是弧形的并且允许气流保持附件和流动从入口通道畅通到进给通道。 沿着后缘设置的凹穴的几何形状被优化以改善冷却。