Multiple expansion film cooling hole for turbine airfoil
US8057181B1 · kind B1 · utility
Assignee
Inventor
Key dates
| Filing date | Nov 7, 2008 |
| Grant date | Nov 15, 2011 |
| Priority date | — |
| Expiry date | Apr 29, 2030 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/202
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A film cooling hole for a turbine airfoil used in a gas turbine engine, where the film cooling hole is formed from a laser with smooth surfaces and without sharp corners, the film hole having a metering section of constant diameter, a first diffusion section having a conical shape, and a spreading section having a contoured clam shell cross sectional shape that opens onto the airfoil surface. The contoured clam shell shaped spreading section includes a raised middle portion with depressions on both sides, and slanted side walls that slant toward the hole opening. The laser cut film cooling hole can be formed after the TBC has been applied.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.