Rotary blade manufacturing method
US10174623B2 · kind B2 · utility
1Cited by
3References
15Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Apr 26, 2016 |
| Grant date | Jan 8, 2019 |
| Priority date | — |
| Expiry date | May 13, 2037 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
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.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.