Method and apparatus for cooling an airfoil
US6280140A · kind A · utility
38Cited by
17References
21Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Nov 18, 1999 |
| Grant date | Aug 28, 2001 |
| Priority date | — |
| Expiry date | Nov 18, 2019 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/2214
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An apparatus and method for cooling a wall for use in a gas turbine engine is provided that includes a cooling air passage having a plurality of segments connected in series by one or more chambers, an inlet aperture, and an exit aperture. The inlet aperture connects the cooling air passage to one side of the wall. The exit aperture connects the cooling air passage to the opposite side of the wall. Cooling air on the inlet aperture side of the wall enters the cooling air passage through the inlet aperture and exits through the exit aperture.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.