Variable geometry guide vane for a gas turbine engine
US7632064B2 · kind B2 · utility
191Cited by
11References
18Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Sep 1, 2006 |
| Grant date | Dec 15, 2009 |
| Priority date | — |
| Expiry date | May 20, 2028 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A variable geometry inlet guide vane for a gas turbine aircraft engine includes an aerodynamic shell for turning inlet flow to a turbine or compressor and an internal spar spaced from the airfoil shell by an air gap. A number of actuation mechanisms grounded to the spar and connected to the inner surface of the aerodynamic shell adjust the shape of the shell in response to varying operating conditions of the engine, imbalanced aerodynamic loading of the shell or vibration or other transient loads on the shell.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.