Shroud assembly for a gas turbine engine
US4497610A · kind A · utility
45Cited by
9References
6Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Feb 16, 1983 |
| Grant date | Feb 5, 1985 |
| Priority date | — |
| Expiry date | Feb 16, 2003 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D25/14
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A shroud assembly for a gas turbine engine consists of a housing having a boundary wall and a gas contacting skin, the wall and skin being in segmented form. The skin consists of a thin metal sheet attached to the boundary wall, and a ceramic gas contacting coating. The skin is impingement cooled by cooling air flowing through apertures in the boundary wall, and the cooling air exhausts into the gas flow through passages. The use of a thin metal sheet with a ceramic coating promotes favorable temperature gradients in the skin enabling the coating to run at optimum conditions for maximum cooling effect.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.