| 发明名称 | Method for making a shaped turbine aerofoil | ||
| 摘要 | According to the method, a turbine aerofoil is made starting from a reference aerofoil, locally reducing the metallic exit angle at the trailing edge in two areas which substantially correspond, in use, to the position of the peaks of the secondary flows in the boundary layer. | ||
| 申请公布号 | US9506348(B2) | 申请公布日期 | 2016.11.29 |
| 申请号 | US201214355983 | 申请日期 | 2012.11.02 |
| 申请人 | GE AVIO S.r.L. | 发明人 | Bertini Francesco |
| 分类号 | F01D5/14 | 主分类号 | F01D5/14 |
| 代理机构 | Davidson Berquist Jackson & Gowdey, LLP | 代理人 | Davidson Berquist Jackson & Gowdey, LLP |
| 主权项 | 1. A method for making a turbine aerofoil starting from a reference aerofoil, comprising the steps of: a) establishing five zones along a trailing edge of the turbine aerofoil with a zone 1 comprising 0-10% thereof, a zone 2 comprising 10-25% thereof, a zone 3 comprising 25-75% thereof, a zone 4 comprising 75-90% thereof, and a zone 5 comprising 90-100% thereof; b) locally reducing the metallic exit angle at the trailing edge with respect to the areas of zones 2 and 4 which correspond substantially, in use, to the position of the peaks of the secondary flows in the boundary layer; and c) increasing the metallic exit angle in the remaining areas of zones 1, 3 and 5 the trailing edge, with respect to that of the reference aerofoil, so as to substantially restore the same average value of the metallic exit angle of the reference aerofoil. | ||
| 地址 | IT | ||