公开(公告)号：US20060275130A1

公开(公告)日：2006-12-07

申请号：US11476110

申请日：2006-06-28

申请人： William Zemitis

发明人： William Zemitis

IPC分类号： F01D5/30

CPC分类号： F01D5/3007 ,  F05D2230/10 ,  F05D2250/70 ,  F05D2260/941

摘要： Blade load path on a gas turbine disk can be diverted to provide a significant disk fatigue life benefit. A plurality of gas turbine blades are attachable to a gas turbine disk, where each of the gas turbine blades includes a blade dovetail engageable in a correspondingly-shaped dovetail slot in the gas turbine disk. In order to reduce gas turbine disk stress, an optimal material removal area is defined according to blade and/or disk geometry to maximize a balance between stress reduction on the gas turbine disk, a useful life of the gas turbine blade, and maintaining or improving the aeromechanical behavior of the gas turbine blade. Removing material from the material removal area effects the maximized balance.

摘要翻译： 可以转向燃气轮机盘上的叶片负载路径以提供显着的盘疲劳寿命益处。 多个燃气轮机叶片可附接到燃气涡轮盘，其中每个燃气轮机叶片包括可接合在燃气涡轮盘中的相应形状的燕尾槽中的叶片燕尾榫。 为了减少燃气轮机盘应力，根据叶片和/或盘几何形状来定义最佳材料去除面积，以最大化燃气轮机盘上的应力减小，燃气轮机叶片的使用寿命和维持或改进之间的平衡 燃气轮机叶片的机械性能。 从材料去除区域去除材料会最大化平衡。

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。

公开(公告)号：US20080101938A1

公开(公告)日：2008-05-01

申请号：US11586765

申请日：2006-10-26

申请人： William Zemitis ,  Christopher Johnson ,  Daniel Snook

发明人： William Zemitis ,  Christopher Johnson ,  Daniel Snook

IPC分类号： F01D5/30

CPC分类号： F01D5/30 ,  F05D2230/10 ,  F05D2260/941

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 1.645 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。 燕尾背切的起始点可以距离基准线在后方至少约1.645英寸。

公开(公告)号：US20080101937A1

公开(公告)日：2008-05-01

申请号：US11586764

申请日：2006-10-26

申请人： William Zemitis ,  Robert St. Louis ,  Daniel Snook

发明人： William Zemitis ,  Robert St. Louis ,  Daniel Snook

IPC分类号： F01D5/30

CPC分类号： F01D5/3007 ,  F05D2230/10 ,  F05D2250/70 ,  F05D2260/941

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 1.539 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。 燕尾背切的起始点可以距离基准线在后方向至少约1.539英寸。