Airfoil leading edge end wall vortex reducing plasma
US7628585B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 15, 2006 |
| Grant date | Dec 8, 2009 |
| Priority date | — |
| Expiry date | Aug 18, 2028 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10S415/914
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A leading edge vortex reducing system includes a gas turbine engine airfoil extending in a spanwise direction away from an end wall, one or more plasma generators extending in the spanwise direction through a fillet between the airfoil and the end wall in a leading edge region near and around a leading edge of the airfoil and near the fillet. The plasma generators being operable for producing a plasma extending over a portion of the fillet in the leading edge region. The plasma generators may be mounted on an outer wall of the airfoil with a first portion of the plasma generators on a pressure side of the airfoil and a second portion of the plasma generators on a suction side of the airfoil. A method for operating the system includes energizing one or more plasma generators to form the plasma in steady state or unsteady modes.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.