System and method for airfoil film cooling
US6629817B2 · kind B2 · utility
16Cited by
8References
13Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jul 5, 2001 |
| Grant date | Oct 7, 2003 |
| Priority date | — |
| Expiry date | Jul 5, 2021 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49341
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An airfoil for a gas turbine engine including an inflection that facilitates enhancing film cooling of the airfoil, without adversely affecting aerodynamic efficiency of airfoil is described. The airfoil includes a generally concave first sidewall and a generally convex second sidewall joined at a leading edge and at a trailing edge of the airfoil. A plurality of cooling openings extend between an internal cooling chamber and an external surface of the first sidewall. One cooling opening extends from the cooling chamber into the inflection at a relatively shallow injection angle with respect the airfoil external surface.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.