Pulse detonation system for a gas turbine engine
US6889505B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Apr 2, 2003 |
| Grant date | May 10, 2005 |
| Priority date | — |
| Expiry date | May 12, 2023 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K7/005
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough includes a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, where at least one stage of circumferentially spaced detonation chambers is disposed therein. The pulse detonation system further includes a shaft rotatably connected to the cylindrical member and a stator configured in spaced arrangement around the forward surface, the aft surface, and the outer circumferential surface of the cylindrical member and a portion of the shaft. The stator has at least one group of ports formed therein which sequentially align with the detonation chambers as the cylindrical member rotates. In this way, detonation cycles are performed in the detonation chambers of each detonation stage so that reaction forces induced by the detonation cycles create a torque which causes the cylindrical member to rotate. Each detonation chamber includes a first open end located adjacent the outer circumferential surface of the cylindrical member and a second closed end located within a middle portion of the cylindrical member.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.