公开(公告)号：US20080101939A1

公开(公告)日：2008-05-01

申请号：US11586793

申请日：2006-10-26

申请人： William Zemitis ,  Steve Byam ,  Patrick Mohr

发明人： William Zemitis ,  Steve Byam ,  Patrick Mohr

IPC分类号： F01D5/30

CPC分类号： F01D5/3015

摘要： A turbine blade that may include an airfoil and a blade dovetail, the blade dovetail being shaped corresponding to a dovetail slot in a turbine disk. The blade dovetail may include a dovetail backcut sized and positioned according to blade geometry to maximize a balance between stress reduction on the disk, stress reduction on the blade, a useful life of the turbine blade, and maintaining or improving the aeromechanical behavior of the turbine blade. A start point of the dovetail backcut, which defines a length of the dovetail backcut along a dovetail axis, may be determined relative to a datum line positioned a fixed distance from a forward face of the blade dovetail along a centerline of the dovetail axis. The start point of the dovetail backcut may be at least approximately 1.215 inches in an aft direction from the datum line.

摘要翻译： 涡轮机叶片，其可以包括翼型件和叶片燕尾榫，叶片燕尾形成对应于涡轮盘中的燕尾槽。 刀片燕尾形可以包括根据叶片几何尺寸和定位的燕尾形后刀，以最大化盘上的应力减小，叶片上的应力减小，涡轮叶片的使用寿命以及维持或改善涡轮机的机械性能之间的平衡 刀。 可以相对于沿着燕尾轴线的中心线与叶片燕尾榫的前面定位的固定距离的基准线来确定燕尾形背切的开始点，其沿着燕尾轴线限定燕尾背部的长度。 燕尾倒背的起点可能距离基准线在后方至少约为1.215英寸。