Gas turbine engine including airfoils having an improved airfoil film cooling configuration and method therefor
US7223072B2 · kind B2 · utility
7Cited by
21References
19Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jan 27, 2004 |
| Grant date | May 29, 2007 |
| Priority date | — |
| Expiry date | Aug 30, 2024 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49995
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An airfoil for a gas turbine engine blade includes a plurality of film cooling holes extending through its outer surface. The film cooling holes are formed by defining at least a first datum structure and a second datum structure, and then forming each film cooling hole at a location on the airfoil outer surface relative to the first and second datum structures. As a result, each film cooling hole has a centerline extending therethrough that forms a compound angle with respect to a tangent to the outer surface, and the distance between the centerlines of each film cooling hole is at least a predetermined minimum distance.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.