Pulse detonation system for a gas turbine engine
US6928804B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Mar 6, 2003 |
| Grant date | Aug 16, 2005 |
| Priority date | — |
| Expiry date | Nov 7, 2023 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K7/02
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough, the pulse detonation system includes an air inlet duct in flow communication with a source of compressed air, the air inlet duct including at least one port formed therein for permitting compressed air to flow therethrough, a fuel injector mounted to the air inlet duct in circumferentially spaced relation to each port, and a device mounted to the air inlet duct in circumferentially spaced relation to each fuel injector for initiating a detonation wave. A rotatable ring member is also positioned in coaxial relation around a portion of the air inlet duct, with the ring member including at least one stage of detonation disposed therein. Accordingly, a detonation wave is produced in each detonation stage and combustion gases following each detonation wave create a torque which causes the ring member to rotate. Each detonation stage in the ring member further includes a plurality of circumferentially spaced detonation ducts extending tangentially from an inner surface of the ring member, wherein the detonation ducts are aligned with each port, the fuel injector and the initia…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.