爆震波点火器管路传播过程数值模拟

推进技术 ›› 2006, Vol. 27 ›› Issue (1): 83-87.

爆震波点火器管路传播过程数值模拟

郭红杰,梁国柱

北京航空航天大学宇航学院北京100083;北京航空航天大学宇航学院北京100083

发布日期:2021-08-15
基金资助:
国家“八六三”基金项目(2002AA726021)

Numerical simulation of detonation propagation in tube of detonation wave igniter

School of Astronautics,Beijing Univ.of Aeronautics and Astronautics,Beijing 100083,China;School of Astronautics,Beijing Univ.of Aeronautics and Astronautics,Beijing 100083,China

Published:2021-08-15

摘要/Abstract

摘要： 为了进一步研究液体火箭发动机爆震波点火器的工作过程,结合实际试验发动机用爆震波点火器的工作条件,在混合比为3,初始氢氧混气压力为0.1MPa情况下,采用常用的两步显式M acCorm ak差分格式和有限速率化学反应动力模型,对爆震波点火器管路中爆震波的传播过程进行了数值模拟,研究了爆震波形成后在一维管路中传播特性及性能参数。从数值模拟结果来看,稳定传播的爆震波温度可达3500K,压力达到2MPa,其传播速度可达3430m/s,从爆震波形成到其传播到2m距离的出口,用时不到0.6m s。并与试验结果进行了对比分析,数值模拟结果和试验结果符合很好,为爆震波点火器的工程设计提供了理论依据。

关键词: 液体推进剂火箭发动机;爆震波;点火器;数值仿真

Abstract: To investigate the process of detonation wave igniter of liquid rocket engine,one-dimensional reacting flow and finite reaction velocity model were used and the two-step explicit MacCormak scheme is adopted to numerically simulate the detonation wave propagation in the tube of the detonation wave igniter,with the factual experimental engine condition in which H₂/O₂ mixture ratio is about 3 and the initial pressure is 0.1MPa.The characteristics of detonation wave in a one-dimension tube with detonation wave formed were studied.The numerical results show that,the stable detonation wave has a high temperature of 3500K and high pressure of 2 MPa,and its propagation velocity is about 3430m/s.It costs less than 0.6ms when the detonation wave arrives at the exit of a 2m-long tube. The numerical results agree well with experimental data and provide theoretical basis for engineering design of detonation wave igniter.

Key words: Liquid propellant rocket engine;Detonation wave;Igniter;Numerical simulation

郭红杰,梁国柱. 爆震波点火器管路传播过程数值模拟[J]. 推进技术, 2006, 27(1): 83-87.