Research On Atomization System Of Pulse Detonation Rocket Engine

Since Hoffman put forward the concept of detonation combustion in 1940, the study of detonation combustion has passed sixty years, many countries have made different progress. However, many key technologies such as spraying and mixture of fuel were awaited to be solved urgently if want to use the new concept engine in the fields of aviation and spaceflight.Focus on the atomization system of Pulse Detonation Rocket Engine (PDRE), combined with detonation performance, this thesis tested performance of each kind of atomization installation for find a best way to be advantageous to detonation performance. Every injector structure was designed independently, the design and the content have the detailed introduction in the thesis.The thesis include three portions: to begin with the Sauter Mean Diameters ( SMD ) in different working conditions were measured using Marvern sizer, compressed air was utilized to model compressed oxygen and water to liquid fuel. The results show that the higher the pressure of air and water, the less the SMD. Based on the verification with detonation experiments, it is concluded that the atomization performance of a swirl nozzle is superior to that of a simple nozzle. Secondly, the influence of injector structure on atomization performance of PDRE is experimentally investigated in this paper. In cold tests, The SMD in different working conditions and different injector structure were measured using Marvern sizer. The results show that the atomization performance of a radial inlet injector is superior to that of a tangential inlet injector. Based on the verification with detonation experiments, the same conclusion was obtained. Finally, fuel was heated to higher than boiling point temperature by the Flash Vaporization System(FVS) and was vaporized as soon as sprayed from nozzle. In this way, the atomization granularity of been heated is smaller than unheated.