Plasma lifted boundary layer gas turbine engine vane
US7766599B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Oct 31, 2006 |
| Grant date | Aug 3, 2010 |
| Priority date | — |
| Expiry date | Nov 27, 2028 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10S415/914
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A plasma boundary layer lifting system includes at least one gas turbine engine vane having a spanwise extending airfoil with an outer surface extending in a chordwise direction between opposite leading and trailing edges and chordwise spaced apart plasma generators for producing a plasma extending in the chordwise direction along the outer surface. Each plasma generator may include inner and outer electrodes separated by a dielectric material disposed within a spanwise extending groove in the outer surface. The airfoil may be hollow having an outer wall and the plasma generators being mounted on the outer wall. A method for operating the system includes forming a plasma extending in the chordwise direction along the outer surface of the airfoil. The method may further include operating the plasma generators in steady state or unsteady modes.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.