Apparatus and method for inhibiting radial transfer of core gas flow within a core gas flow path of a gas turbine engine
US6419446B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 21, 1999 |
| Grant date | Jul 16, 2002 |
| Priority date | — |
| Expiry date | Dec 21, 2019 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10S415/914
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method for inhibiting radial transfer of core gas flow away from a center radial region and toward the inner and outer radial boundaries of a core gas flow path within a gas turbine engine is provided that includes the steps of: (1) providing a flow directing structure that includes an airfoil that abuts a wall surface, said airfoil having a leading edge, a pressure side, and a suction side; and (2) increasing the velocity of the core gas flow in the area where the leading edge of the airfoil abuts the wall. Increasing the velocity of the core gas flow in the area where the leading edge of the airfoil abuts the wall impedes the formation of a pressure gradient along the surface of the airfoil that forces core gas from the center region of the core gas toward the wall. The apparatus includes apparatus for diverting core gas flow away from the area where the airfoil abuts the wall.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.