| 发明名称 |
GAS TURBINE ENGINE TRUNCATED AIRFOIL FILLET |
| 摘要 |
An integrally bladed rotor includes a rim integral with a web that extends radially inward to a bore. The rim provides an end wall from which integral blades extend radially outward to a tip. The blades have an airfoil that extends in a chord-wise direction from a leading edge to a trailing edge. A fillet circumscribes the airfoil and joins the airfoil to the end wall. The fillet is at one of the leading edge and the trailing edge is truncated at least 50% in an axial direction to provide a face of the rim. |
| 申请公布号 |
US2016208614(A1) |
申请公布日期 |
2016.07.21 |
| 申请号 |
US201514597633 |
申请日期 |
2015.01.15 |
| 申请人 |
United Technologies Corporation |
发明人 |
Potter Christopher L.;Espinoza Michael |
| 分类号 |
F01D5/14;F02C3/06;F01D5/02;F04D29/32;F01D9/02 |
主分类号 |
F01D5/14 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. An integrally bladed rotor comprising:
a rim integral with a web that extends radially inward to a bore, the rim providing an end wall from which integral blades extend radially outward to a tip, the blades have an airfoil that extends in a chord-wise direction from a leading edge to a trailing edge, a fillet circumscribes the airfoil and joins the airfoil to the end wall, the fillet at one of the leading edge and the trailing edge truncated at least 50% in an axial direction to provide a face of the rim. |
| 地址 |
Hartford CT US |
