Curved film cooling holes for gas turbine engine vanes
US5281084A · kind A · utility
28Cited by
30References
9Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jul 13, 1990 |
| Grant date | Jan 25, 1994 |
| Priority date | — |
| Expiry date | Jul 13, 2010 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2250/71
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method and apparatus for film cooling of an aerodynamically shaped airfoil uses a plurality of curved slots extending through the airfoil in an area upstream of the high curvature region of the airfoil, i.e., in an area of low Mach number of the gas stream passing over the airfoil surface. The curved slots are configured to inject cooling air at an angle of about 16.5 degrees. The cooling air is injected at a blowing ratio in excess of 1.0 and yet is effective to form a film on the vane surface.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.