Research status of oblique detonation combustion and oblique detonation engine
The development of higher performance aspirated hypersonic propulsion has become the most important thing in the development of hypersonic vehicles in the future.The existing scramjet engine based on kerosene fuel is mainly organized in detonation mode.Under the condition of high inflow Mach number(Ma ≥8),it is difficult to fully release and utilize fuel energy due to the high-temperature dissociation and chemical non-equilibrium effect of high inflow total temperature zone.In contrast,combustion with inclined detonation structure is closer to constant volume combustion.With the advantages of fast combustion heat release rate and high thermal cycle efficiency,it is an ideal combustion mode which can be applied to high Mach number inspiratory power.Oblique detonation engine can significantly shorten the length of the com-bustion chamber and reduce the heat release area,which is a promising aspirating power scheme for high Mach number aircraft.Among them,the matching design of each component in the internal flow path of ob-lique detonation engine,fuel injection-mixing,initiation and residence of oblique detonation wave are the key technologies in the development of oblique detonation engine,and are the research hotspots in hyper-sonic field at present.However,due to the high speed,high total temperature and total pressure flow condi-tions and the strong discontinuous and high-speed propagation characteristics of detonation waves in the flow field,the existing experimental and numerical simulation research methods are difficult to carry out detailed research on the combustion flow mechanism,thus limiting the disclosure of relevant control mech-anisms and the establishment of high-precision models,making it difficult to develop oblique detonation engine engineering.There are still many places worth exploring in the current research,and this paper summarizes and puts forward relevant suggestions for the next research.
万方数据
维普
