流场不均匀对液体火箭发动机纵向振荡燃烧影响及控制  

Influence and control of non-uniform flow field on longitudinal combustion instability of liquid rocket engines

作　　者：李龙飞 杨宝庆 葛树宏 刘佩进[1] 刘新华 LI Longfei;YANG Baoqing;GE Shuhong;LIU Peijin;LIU Xinhua(School of Astronautics,Northwestern Polytechnical University,Xi’an 710072,China;National Key Laboratory of Science and Technology on Liquid Rocket Engines,Xi’an Aerospace Propulsion Institute,China Aerospace Science and Technology Corporation,Xi’an 710100,China)

机构地区：[1]西北工业大学航天学院,西安710072 [2]中国航天科技集团有限公司西安航天动力研究所液体火箭发动机技术重点实验室,西安710100

出　　处：《航空动力学报》2023年第1期223-229,共7页Journal of Aerospace Power

基　　金：民用航天重点基础研究(D010201)。

摘　　要：针对常温推进剂发动机推力室再生冷却和撞击式喷注器结构,分析了推力室身部与喷注器对接部位的流场特性,对流场均匀性进行了实验测量。结果表明:推力室身部再生冷却通道出口压力存在约0.15 MPa周向不均匀。身部出口节流显著提高局部流速,使喷注器面氧化剂湍流度和不均匀性增加,进而改变燃烧特性。通过撞击喷注单元雾化试验,获得了18 m/s的推进剂入口边界流速。基于喷注器流场均匀性,提出控制推进剂流速,降低不均匀性,进而抑制纵向高频燃烧不稳定性的控制方法。发动机热试结果表明,采用(15±1) m/s的推进剂入口流速,控制方法抑制了纵向高频燃烧不稳定性。The vortex instability and pressure oscillation in the flow field are one of the important reasons for the high frequency longitudinal combustion instability of liquid rocket engine. Considering the regenerative cooling channel and impinging jet injectors in the thrust chamber ofnormal temperature propellant rocket engine,the flow field of the connecting part between the thrust chamber body and the injector was analyzed, and its uniformity were measured experimentally. Results showed that the circumferential non-uniform pressure at outlet of regenerative cooling channel was about 0.15 MPa. The use of throttling at the outlet of the cylindrical section of the thrust chamber can significantly increase the local fluid velocity and the turbulence and non-uniformity of the oxidant at the injector,thereby changing the combustion characteristics. The atomization test of impact injection unit was carried out,and the propellant inlet boundary velocity of 18 m/s was obtained. Based on the flow field uniformity of the injector,a control method of suppressing the longitudinal high frequency combustion instability was proposedby controlling the propellant flow rate and reducing the non-uniformity. The engine thermal test results showed that the control method suppressed the longitudinal high frequency combustion instability of the thrust chamber at the propellant inlet flow rate of(15±1) m/s.

关 键 词：液体火箭发动机 推力室 撞击式喷注器 纵向燃烧不稳定性 不均匀性 

分 类 号：V434.1[航空宇航科学与技术—航空宇航推进理论与工程]