| 发明名称 | Turbine bucket and method for balancing a tip shroud of a turbine bucket | ||
| 摘要 | The present application and the resultant patent provide a turbine bucket for a gas turbine engine. The turbine bucket may include an airfoil, a tip shroud positioned radially outward from the airfoil, and a seal rail positioned radially outward from the tip shroud and extending in a generally tangential direction from a first end to a second end of the tip shroud. The seal rail may include a maximum axial thickness at a location positioned between the first end and the second end and offset from the airfoil in the generally tangential direction. The present application and the resultant patent further provide a gas turbine engine and a method for balancing a tip shroud of a turbine bucket of a gas turbine engine. | ||
| 申请公布号 | US9464530(B2) | 申请公布日期 | 2016.10.11 |
| 申请号 | US201414185161 | 申请日期 | 2014.02.20 |
| 申请人 | General Electric Company | 发明人 | Kareff Spencer Aaron;Piersall Matthew Robert;Werner Danielle |
| 分类号 | F01D5/30;F01D5/20;F01D5/22 | 主分类号 | F01D5/30 |
| 代理机构 | Sutherland Asbill & Brennan LLP | 代理人 | Sutherland Asbill & Brennan LLP |
| 主权项 | 1. A turbine bucket for a gas turbine engine, the turbine bucket comprising: an airfoil; a tip shroud positioned radially outward from the airfoil; and a seal rail positioned radially outward from the tip shroud and extending in a generally tangential direction from a first end to a second end of the tip shroud, wherein the seal rail comprises a maximum axial thickness at a location positioned between the first end and the second end of the tip shroud and entirely offset from a pressure side or a suction side of the airfoil in the generally tangential direction. | ||
| 地址 | Schenectady NY US | ||