利索-全球专利检索

  1. 登录
  2. 注册
发明授权
CN101173611B 用于减少叶片/圆盘应力的叶片/圆盘燕尾榫顶槽 失效 - 权利终止

用于减少叶片/圆盘应力的叶片/圆盘燕尾榫顶槽
摘要：
本发明涉及一种用于减少叶片/圆盘(9FA，第一级)应力的叶片/圆盘燕尾榫顶槽，其中涡轮机叶片(12)，包括翼面(18)和叶片燕尾榫(16)，叶片燕尾榫(16)具有与涡轮机圆盘(10)中的燕尾槽(14)相匹配的形状。叶片燕尾榫(16)包括燕尾榫顶槽(22)，按照叶片几何结构设定所述燕尾榫顶槽的尺寸和位置，使圆盘(10)上的应力减少、叶片(12)上的应力减少、涡轮机叶片(12)的使用寿命与维持或者提高涡轮机叶片(12)的空气动力学特性之间的平衡达到最大化。相对于基准线从叶片燕尾榫(16)的前面起沿着燕尾榫轴的中心线的一固定距离确定了限定沿燕尾榫轴的燕尾榫顶槽(22)长度的燕尾榫顶槽(22)的起始点。燕尾榫顶槽(22)的起始点从基准线起在向后方向至少大约1.539英寸处。
摘要（英）：

The present invention relates to dovetail tenon backcut for reducing tension of blade/disk (9FA, a first level), where a turbine blade (12) that may include an airfoil (18) and a blade dovetail (16), the blade dovetail (16) being shaped corresponding to a dovetail slot in a turbine disk. The blade dovetail (16) may include a dovetail backcut (22) sized and positioned according to blade geometry to maximize a balance between stress reduction on the disk (10), stress reduction on the blade (12), 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 (22), 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 (22) may be at least approximately 1.539 inches in an aft direction from the datum line.

公开/授权文献
0/0