Study on coupling characteristics of supersonic inlet and pulse detonation combustor

Coupling model for two-dimensional mixed-compression supersonic inlet with Mach number of 2.5 at design point and pulse detonation combustor was established, three working schemes were designed to investigate multi cycle process by using unsteady numerical simulation chemical reaction. The results show that the following two measurements can both restrain back-propagating compression wave broaden stability margin increase frequency, one which is pressure relief outlet combustor, other valve combustor. Nevertheless, former will lose thrust, while latter greatly thrust. Meanwhile, reflect in production; turbulence make gas entrained into diffuser section moment opening valve. However, reflected hot production not affect velocity shape wave. Furthermore, period initiation propagation, blockage ratio physical obstructions should be expanded as much possible. At same time, flow blocked resistance.