斜爆震燃烧与斜爆震发动机研究进展

Research status of oblique detonation combustion and oblique detonation engine

发展更高性能的吸气式高超动力成为未来高超声速飞行器研制的重中之重。现有基于煤油燃料的超燃冲压发动机,主要以爆燃模式组织燃烧,在高来流马赫数(Ma≥8)条件下,将面临高来流总温带来的高温离解和化学非平衡效应所带来燃料的能量难以充分释放和利用的难题,相比之下,斜爆震组织燃烧更接近于等容燃烧,具有燃烧释热速率快、热循环效率高等优势,是一种可应用于高马赫数吸气式动力的理想燃烧模式。斜爆震发动机能够显著缩短燃烧室长度,减少释热面积,是高马赫数飞行器极具潜力的吸气式动力方案。其中,斜爆震发动机内流道各部件的匹配设计、燃料喷注-混合、斜爆震波的起爆与驻定等是斜爆震发动机研制的关键技术,是当前高超声速领域的研究热点。但由于其面临的高速、高总温总压的来流条件以及爆震波在流场中的强间断与高速传播特性等,现有试验与数值模拟研究手段难以开展精细的燃烧流动机制研究,进而限制了相关控制机理的揭示与高精度模型的建立,使得斜爆震发动机工程研制较为困难,当前研究仍存在许多值得探讨的地方,文章在综述的同时对下一步研究提出相关建议。

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 combustion 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 oblique 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 hypersonic field at present.However,due to the high speed,high total temperature and total pressure flow conditions 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 mechanisms 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.