Dual mode combustion operation of a pulse detonation combustor in a hybrid engine
US7950219B2 · kind B2 · utility
32Cited by
4References
22Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Oct 31, 2006 |
| Grant date | May 31, 2011 |
| Priority date | — |
| Expiry date | Mar 31, 2030 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R7/00
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A dual mode combustor of a gas turbine engine contains at least one dual mode combustor device having a combustion chamber, a fuel air mixing element, a high frequency solenoid valve and a fuel injector. During a first mode of operation the dual mode combustor device operates in a steady, constant pressure deflagration mode, receiving its fuel from the fuel injector. In a second mode of operation the dual mode combustor device operates in a pulse detonation mode, receiving its fuel from the high frequency solenoid valve.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.