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 b...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 per-formance 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 1540-1750 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 1800 N,1750 s and 313 kg/(m2.s).A nozzle can greatly improve the propulsion performance.展开更多
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 t...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 advance- ments 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 engi- neerin~ applications of CRDE are 13rovided.展开更多
To investigate the impact of combustor width on continuous rotating detonation(CRD)fueled by ethylene and air,a series of 3 D simulations are conducted by changing the inner cylinder radius of an annular combustor whi...To investigate the impact of combustor width on continuous rotating detonation(CRD)fueled by ethylene and air,a series of 3 D simulations are conducted by changing the inner cylinder radius of an annular combustor while retaining the same outer cylinder radius.The results show that the CRD wave propagates more steadily and faster as the combustor width increases.The high-temperature zone at the backward-facing step preheats the propellants and contributes to the steady propagation of the CRD wave in 25-and 30-mm wide combustors.The highest and the lowest velocities are obtained in the30-and 15-mm wide combustors at,respectively,1880.27 and 1681.01 m/s.On the other hand,the average thrust decreases as the combustor width increases.The highest thrust is obtained in the 15-mm wide combustor while the lowest is in the 30-mm wide combustor,at 758.06 and 525.93 N,respectively.Nevertheless,the thrust is much more stable in the 25-and 30-mm wide combustors than in the 15-and 20-mm wide combustors.展开更多
基金Aeronautical Science Foundation of China(2008ZH71006)
文摘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 per-formance 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 1540-1750 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 1800 N,1750 s and 313 kg/(m2.s).A nozzle can greatly improve the propulsion performance.
基金co-supported by the Aeronautical Science Foundation of China(No.2008ZH71006)the National Natural Science Foundation of China(No.91441110)the Aerospace Innovation Fund of China(No.SY41YYF2014009)
文摘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 advance- ments 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 engi- neerin~ applications of CRDE are 13rovided.
基金supported by the National Natural Science Foundation of China(No.51776220)the Postgraduate Scientific Research Innovation Project of Hunan Province,China。
文摘To investigate the impact of combustor width on continuous rotating detonation(CRD)fueled by ethylene and air,a series of 3 D simulations are conducted by changing the inner cylinder radius of an annular combustor while retaining the same outer cylinder radius.The results show that the CRD wave propagates more steadily and faster as the combustor width increases.The high-temperature zone at the backward-facing step preheats the propellants and contributes to the steady propagation of the CRD wave in 25-and 30-mm wide combustors.The highest and the lowest velocities are obtained in the30-and 15-mm wide combustors at,respectively,1880.27 and 1681.01 m/s.On the other hand,the average thrust decreases as the combustor width increases.The highest thrust is obtained in the 15-mm wide combustor while the lowest is in the 30-mm wide combustor,at 758.06 and 525.93 N,respectively.Nevertheless,the thrust is much more stable in the 25-and 30-mm wide combustors than in the 15-and 20-mm wide combustors.
