Preliminary Experimental Investigation on Detonation Initiation in the Ejector of a Pulse Detonation Rocket Engine
-
Yu Yan
and
Yang Mu
Abstract
A small pulse detonation rocket engine (PDRE) was used as a predetonator to initiate detonation in its ejector. The detonation products discharged from the PDRE was not only ignition source for the ejector but also primary flow which entrained air from environment into the ejector. Stoichiometric liquid kerosene and gaseous oxygen were used as reactants for the PDRE. While in the ejector injected liquid kerosene was used as fuel and entrained air was used as oxidizer. Reactants in the ejector were ignited by the detonation wave and products discharged from the PDRE. Detonation was successfully initiation in present experiments. It was found that flame propagation upstream at the entrance of the ejector was inevitable, which affected the detonation initiation process in the ejector. Disks with orifices were placed at the entrance of the ejector to weaken the flame propagation upstream effect, which would affect the air flow entraining process, but the results show it worked.
©[2012] by Walter de Gruyter Berlin Boston
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- Statistical Turbofan Architecture Management for Use in a Supercirculation Wing Aircraft
- Calculating High Speed Centrifugal Compressor Performance from Averaged Measurements
- Preliminary Experimental Investigation on Detonation Initiation in the Ejector of a Pulse Detonation Rocket Engine
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Articles in the same Issue
- Masthead
- Flow Field around a Blunt-nosed Body with Spike
- The Flow Analysis and Performance Improvement of the Flow Return System in High Pressure Fans
- Numerical Investigation of Heat Transfer Characteristic on Scalelike Platelet Inner Duct
- Analytical Calculation of Stall-inception and Surge Points for an Axial-flow Compressor Rotor
- Fatigue Life Estimation of an Aircaft Engine Under Different Load Spectrums
- Numerical Simulation of Tangling in Jet Engine Turbines
- Statistical Turbofan Architecture Management for Use in a Supercirculation Wing Aircraft
- Calculating High Speed Centrifugal Compressor Performance from Averaged Measurements
- Preliminary Experimental Investigation on Detonation Initiation in the Ejector of a Pulse Detonation Rocket Engine
- An Application of Fuzzy Fault Tree Analysis to Uncontained Events of an Areo-Engine Rotor
