A Research On Detonation Initiation Method Of Pulse Detonation Engine

By comparing with the current propulsion systems, Pulse Detonation Engine (PDE) has more performance advantages because of its simple structure, high thermal efficiency, low specific fuel consumption, large thrust, large motor cross section, large unit mass thrust as well as the possibilities in reducing cost of aircraft manufacture and mission performance. Therefore, it has become a research focus in many countries.In this thesis, various research processes on PDE in China and abroad were summarized, and challenges within its applications were also addressed. The structure of detonation wave and thermal cycle process of PDE were analyzed. The mass flow controller and display produced by Switzerland Sensiron were used to improve the air supply system and promote the simulation condition, to be closer to the real operating condition of PDE. The pre-combustion jet initiation method was finally selected by compared with several detonation initiation methods including high energy initiation, shock reflection detonation, multi-pipe detonation wave, multi-spot ignition and pre-combustion jet detonation initiations. Three different single cycle PDE assemblies were established to investigate the influence of pre-combustion jet in the branching pipe on detonation formation in the main tube. Operations of PDE under different conditions were simulated through changes in blockage ratio, fuel type, chemical equivalence ratio, inlet pressure, ignition energy, etc. The influence of such factors on shock pressure and thrust were finally analyzed through the data measured.