Abstract
The duty cycle for C10H19/oxygen injection and time sequence for injection, mixing and ignition to produce two-phase, fully-developed detonations are investigated in a pulse detonation rocket engine (PDRE) model. The The PDRE test model is 25mm in inner diameter and l.lm long. The solenoid valves are employed to control intermittent supplies of propellants and purge gas. The spark igniter has ignition energy of around 50mJ. The solenoid valves and igniter are controlled by a control system. Under some given supply conditions, the detonability limits in terms of injection duty cycle and the controlling method are obtained. From fundamental analysis, these factors influence the operation of PDRE essentially by appropriate equivalence ratio and mixing. The experimental results show that to gain reliable detonations, first of all, the injection duty cycles for C10H19 and oxygen should ensure sufficient filling and then the injection time phases and duty cycles should be kept as close as possible to attain effective mixing.
Original language | English |
---|---|
Pages (from-to) | 277-282 |
Number of pages | 6 |
Journal | International Journal of Turbo and Jet Engines |
Volume | 23 |
Issue number | 4 |
DOIs | |
State | Published - 2006 |
Keywords
- Detonability limits
- Experimental investigation
- Injection duty cycle
- Mixing
- Pulse detonation rocket engine