推进剂总质量流量对连续旋转爆轰发动机性能影响实验研究

Experimental Research on Effects of Propellant Total Mass Flow Rate on Performance of Continuous Rotating Detonation Engine

关键词:  推进剂总质量流量  连续旋转爆轰发动机  爆轰波  传播特性  推力性能

Key words:  Propellant total mass flow rate  Continuous rotating detonation engine  Detonation wave  Propagation characteristics  Thrust performance

摘要:

为了研究推进剂总质量流量对连续旋转爆轰发动机(CRDE)爆轰波传播特性以及推力性能的影响，在环缝-喷孔对撞式喷注H2/Air的CRDE上开展了一系列实验。基于测量的高频压力信号，详细分析了不同推进剂总质量流量工况下爆轰波传播的典型波形、速度与频率以及稳定性。测量了CRDE长时间工作产生的推力，并讨论燃料比冲的变化情况。实验结果表明，当量比不变时，随着总质量流量的增加，爆轰波依次表现传播方向转变、双波对撞向单波同向转变、单波同向、以及双波同向与单波同向共存四种传播模式，平均传播速度和频率呈现出先增大后减小的趋势；推进剂总质量流量偏高或偏低，爆轰波均表现为不稳定传播模态。发动机产生的平均推力随着总质量流量的增大而呈线性增大，燃料比冲则是先增大后减小，当推进剂总质量流量为593.60g/s，获得基于燃料的比冲最大为5159s。

Abstract:

In order to investigate the effects of propellant total mass flow rates on the thrust performance of continuous rotating detonation engine (CRDE) and propagation characteristics of detonation wave， a series of experiments have been carried out in H2/Air CRDE with slit-orifice collision injection mode. Based on the high frequency pressure signals， the rotating detonation wave typical waveform， propagation velocity and frequency， as well as the propagation stability， were analyzed in detail under different propellant total mass flow rates. Afterwards， the thrust generated by CRDE for a long time was measured， and the fuel-based specific impulse was discussed. Experimental results indicate that in the case of constant equivalence ratio， as the propellant total mass flow increases， the detonation wave propagation mode in sequence includes change of propagation direction， dual-wave collision to single wave one-way transformation， single-wave one-way mode， and single/dual-wave hybrid mode， simultaneously， the average propagation velocity and frequency increase first and then decrease. If the propellant total mass flow rate is too high or too low， the detonation wave shows unstable propagation mode. The average thrust of CRDE increases linearly with the increase of the propellant total mass flow rate， however， the fuel-based specific impulse increases first and then decreases. When the total mass flow of propellant is 593.60g/s， the maximum fuel-based specific impulse is 5159s.