Off-axis pulse detonation configuration for gas turbine engine
US7200987B2 · kind B2 · utility
0Cited by
11References
65Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jun 18, 2004 |
| Grant date | Apr 10, 2007 |
| Priority date | — |
| Expiry date | Dec 8, 2024 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K9/78
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The present invention is a gas turbine engine system containing a compressor stage, a pulse detonation stage, and a turbine stage. During operation of the engine system, compressed flow from the compressor stage is directed to at least one off-axis pulse detonation tube in the pulse detonation stage. The off-axis pulse detonation tube detonates a mixture containing the compressed flow and a fuel to create a detonation wave, which is routed to an inlet portion of a reverse flow turbine. The exhaust flow from the reverse flow turbine is then directed away from the engine through ducting.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.