环形燃烧室中圆台斜爆震燃烧特性研究

In order to meet the development requirements of wide-range detonation combined engine，truncated cone induced oblique detonation wave（ODW）combustion structure suitable for axis symmetric annular combustor is proposed for the first time. The feasibility of truncated cone induced stationary ODW combustion and its difference with wedge and conical oblique detonation combustion under flight Mach number 7 were verified by numerical simulation. The initiation and stationary characteristics of truncated cone induced ODW were studied from two aspects of geometry and inflow parameters. The results show that，compared with the cone and wedge，the truncated cone in the annular combustor can realize the acceleration initiation and stationary of ODW at the same time in the low flight Mach number condition. The compression upstream and expansion downstream the truncated cone leads the truncated cone induced ODW showing a special initiation zone structure of detachment without travelling forward. The increase of the inner diameter of the truncated cone，the angle of the truncated cone，the compression degree of incoming flow and the equivalent ratio are all beneficial to the initiation of ODW induced by the truncated cone. At the same time，the structure of the initiation zone also shows a change law from gradual change to abrupt change and then to stable detachment，and the corresponding initiation distance is gradually shortened and the ODW angle is gradually increased.