Cooled shroud for a gas turbine engine
US4318666A · kind A · utility
18Cited by
5References
5Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Jun 17, 1980 |
| Grant date | Mar 9, 1982 |
| Priority date | — |
| Expiry date | Jun 17, 2000 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/203
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A cooled shroud for a gas turbine engine comprises an annular metallic supporting member having holes therethrough for the flow of cooling air and a layered coating on its inner face. The layered coating comprises a first layer of porous material through which the cooling air may permeate, and a second layer of impermeable ceramic covering all but selected areas of the surface of the first layer. In this way the cooling air is largely constrained to flow along the porous material to provide good cooling with relatively low air flow.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.