| 发明名称 |
ROTARY BLADE MANUFACTURING METHOD |
| 摘要 |
The present invention provides a method of designing a manufacturing geometry for a tip portion of a rotary blade for a gas turbine engine. The method comprises first devising a theoretical hot running geometry of the tip portion at a specified design condition. Next, the theoretical operational forces acting on the theoretical hot running geometry at the specified design condition are calculated e.g. using CFD software. Then, the manufacturing geometry is determined (e.g. using FEA analysis) using the calculated theoretical operational forces. |
| 申请公布号 |
US2016341050(A1) |
申请公布日期 |
2016.11.24 |
| 申请号 |
US201615138857 |
申请日期 |
2016.04.26 |
| 申请人 |
ROLLS-ROYCE plc |
发明人 |
SCOTT John M. |
| 分类号 |
F01D5/20;F04D29/52;F04D29/32;F04D29/08;F01D5/34;F01D11/18 |
主分类号 |
F01D5/20 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A method of designing a manufacturing geometry for a tip portion of a rotary blade for a gas turbine engine, said method comprising:
devising a theoretical hot running geometry of the tip portion at a specified design condition; calculating the theoretical operational forces acting on the theoretical hot running geometry at the specified design condition; and determining the manufacturing geometry using the calculated theoretical operational forces. |
| 地址 |
London GB |
