Small gas turbine engine with multiple burn zones
US7568343B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 12, 2005 |
| Grant date | Aug 4, 2009 |
| Priority date | — |
| Expiry date | Jan 31, 2027 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2250/80
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A small gas turbine engine for use in an UAV such as a cruise missile, the gas turbine having a combustor forming a primary burn zone and a secondary burn zone, and in which fuel is injected into both the primary and the secondary burn zones by either a rotary cup injector or a plurality of fuel injector nozzles. The secondary burn zone with separate fuel injection allows for the diameter of the engine to be reduced in size but still allow for adequate power and efficiency to be reached for powering the vehicle. Air flow from the compressor is used to cool the combustor walls before being injected into the combustor, and to pass through and cool the guide nozzles and a main bearing located near the hot section of the combustor prior to being introduced into the combustor.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.