气液针栓喷注器在节流水平下的雾化角模型分析  

Analysis of Spray Angle Model of Gas-liquid Pintle Injector at Throttling Level

作　　者：张波涛 李平 杨宝娥 ZHANG Bo-tao;LI Ping;YANG Bao-e(National Key Laboratory of Science and Technology on Liquid Rocket Engines,Xi’an Aerospace Propulsion Institute,Xi’an 710100,China;Academy of Aerospace Liquid Propulsion Technology,Xi’an 710100,China)

机构地区：[1]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 [2]航天推进技术研究院,西安710100

出　　处：《宇航学报》2021年第2期249-258,共10页Journal of Astronautics

基　　金：国家重点基础研究发展计划(613193);国家自然科学基金(11502186)。

摘　　要：为了实现气液针栓喷注器在节流水平下雾化角的准确预测,首先基于控制体分析从动量守恒出发建立了中心推进剂偏转角理论模型,在获得中心推进剂偏转角的基础上建立了雾化角理论模型,并通过试验结果引入变形因子C,最后根据试验结果和数值模拟结果验证了两个模型的准确性。结果表明:中心推进剂偏转角主要受节流水平影响,雾化角主要受动量比和中心推进剂偏转角影响;液束与气膜撞击后变形使液束有效动量小于初始动量,根据试验结果得到变形因子C=0.8,中心推进剂偏转角理论模型和雾化角理论模型的预测值均与试验及数值模拟结果吻合很好,模型可为气液针栓喷注器的理论研究和工程设计提供参考。In order to accurately predict the spray angle of a gas-liquid pintle injector at throttling level,based on the control volume analysis,a theoretical model of central propellant deflection angle is established from the momentum equations firstly.In addition,the theoretical model of spray angle is further analyzed based on the central propellant deflection angle.The deformation factor C is obtained by the experimental results.Finally,the accuracy of the two models is verified according to the results of the test and numerical simulation.The results show that the central propellant deflection angle is mainly dominated by the throttling level.The spray angle is mostly affected by the momentum ratio and central propellant deflection angle.The liquid jet deforms after colliding with the gas film,which causes the effective momentum to be smaller than the initial momentum.According to the experimental results,the recommended value of the deformation factor is C=0.8.The predicted values of the theoretical models of central propellant deflection angle and spray angle are in good agreement with the experimental and numerical simulation results.These models can provide enlightenment for the theoretical research and engineering design of gas-liquid pintle injector.

关 键 词：液体火箭发动机 气液针栓喷注器 中心推进剂偏转角 雾化角 动量比 

分 类 号：V434.3[航空宇航科学与技术—航空宇航推进理论与工程]