Method and apparatus for cooling a wall within a gas turbine engine
US6402470B1 · kind B1 · utility
142Cited by
38References
15Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Oct 5, 1999 |
| Grant date | Jun 11, 2002 |
| Priority date | — |
| Expiry date | Oct 5, 2019 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/2214
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A cooling circuit is provided disposed between a first wall portion and a second wall portion of a wall for use in a gas turbine engine, one or more inlet apertures, and one or more exit apertures. The inlet aperture(s) provides a cooling airflow path into the cooling circuit and the exit aperture(s) provides a cooling airflow path out of the cooling circuit. The cooling circuit includes a plurality of first pedestals extending between the first wall portion and the second wall portion. The first pedestals are arranged in one or more rows.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.