Thrust augmentor having swirled flows for combustion stabilization
US4170109A · kind A · utility
6Cited by
9References
10Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Nov 9, 1977 |
| Grant date | Oct 9, 1979 |
| Priority date | — |
| Expiry date | Nov 9, 1997 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/18
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A thrust augmentor for a turbofan, gas turbine engine is disclosed. Techniques for mixing and burning dissimilar density gases in a thrust augmentor are developed. In accordance with one specific teaching the flame front in a swirl augmentor is stabilized by a continuously operative pilot burner. The pilot burner is positioned in the radially outward portion of the augmentor.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.