Infrared suppression system for a gas turbine engine
US4002024A · kind A · utility
33Cited by
10References
9Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | May 21, 1975 |
| Grant date | Jan 11, 1977 |
| Priority date | — |
| Expiry date | May 21, 1995 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64D2033/045
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An infrared suppression system is provided for an aircraft gas turbine engine for reducing the level of emitted infrared radiation from the engine exhaust. The hot exhaust stream emitted from the engine is mixed with the cooling airflows received from a plurality of sources in order to more effectively reduce the level of emitted infrared radiation. In addition, the infrared suppression system prohibits a direct line of sight back into the core engine.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.