The rotating propagation of a continuous detonation engine(CDE) with different types of nozzles is investigated in three-dimensional numerical simulation using a one-step chemical reaction model.Flux terms are solved by the so-called monotonicity-preserving weighted essentially non-oscillatory(MPWENO) scheme.The simulated flow field agrees well with the previous experimental results.Once the initial transient effects die down,the detonation wave maintains continuous oscillatory propagation in the annular chamber as long as fuel is continuously injected.Using a numerical flow field,the propulsion performance of a CDE is computed for four types of nozzles,namely the constant-area nozzle,Laval nozzle,diverging nozzle and converging nozzle.The gross specific impulse of the CDE ranges 1 540-1 750 s and the mass flux per square meter ranges 313-330 kg/(m2·s) for different nozzles.Among these four types of nozzles,Laval nozzle performs the best,and these parameters are 1 800 N,1 750 s and 313 kg/(m2·s).A nozzle can greatly improve the propulsion performance.
Continuously rotating detonation engine(CRDE) is a focus for concern in the field of aerospace propulsion. It has several advantages, including one-initiation, high thermal efficiency and simple structure. Due to these characteristics, it is expected to bring revolutionary advancements to aviation and aerospace propulsion systems and now has drawn much attention throughout the world. In this paper, an overview of the development of CRDE is given from several aspects:basic concepts, applications, experimental studies, numerical simulations, and so on. Representative results and outstanding contributions are summarized and the unresolved issues for further engineering applications of CRDE are provided.
