两相脉冲爆震火箭发动机性能实验

Experimental investigation on the performance of two-phase pulse detonation rocket engine

为了获得脉冲爆震火箭发动机(PDRE)的性能参数,采用液态煤油为燃料、氧气为氧化剂、压缩氮气为隔离气体,进行了一系列多循环爆震实验。使用孔板流量计测量煤油流量,使用集气法测量氧气流量,使用动态压电式压力传感器测量了爆震室轴向的沿程压力,使用火焰温度及水蒸气浓度红外光谱测量仪测量爆震管出口平面的尾焰温度,使用动态压电式推力传感器测量PDRE所产生的瞬时推力。实验获得PDRE不同频率下的平均推力和比冲。实验结果表明:爆震压力和温度随着工作频率的变化而有所变化,填充系数对于PDRE比冲大小有着显著影响。采用爆震室部分填充的策略,可以显著地提高发动机比冲。

Utilizing liquid kerosene as the fuel,oxygen as oxidizer and nitrogen as purge gas,a series of multi-cycle detonation experiments were conducted to obtain the performance parameters of pulse detonation rocket engine(PDRE).The mass flow of liquid kerosene was measured by orifice meter and the mass flow of oxygen was measured based on the method of gas collection.The detonation chamber pressure traces were recorded by dynamic piezoelectric pressure transducers.Pulsed temperature test was employed to measure pulsed temperature at the exhaust plume of PDRE.A dynamic piezoelectric thrust transducer was used to record the transient thrust produced by PDRE.The average thrust and specific impulse of PDRE with different operation frequency were obtained by experiments.The experimental results indicated that detonation pressure and temperature were varied with the operation frequency of PDRE,and the fill fraction has a significant influence on the specific impulse of PDRE.With the strategy of partial filling in detonation tube,the specific impulse can be remarkably enhanced.