自燃推进剂模型燃烧室高频纵向燃烧不稳定性  

High frequency longitudinal combustion instability of modeled hypergolic propellants combustor

作　　者：汪广旭 谭永华 庄逢辰 陈宏玉 杨宝娥 洪流 陈建华 WANG Guangxu;TAN Yonghua;ZHUANG Fengchen;CHEN Hongyu;YANG Baoe;HONG Liu;CHEN Jianhua(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;Academy of Aerospace Propulsion Technology,China Aerospace Science and Technology Corporation,Xi’an 710100,China;Department of Aerospace Science and Technology,Space Engineering University,Beijing 101416,China)

机构地区：[1]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 [2]中国航天科技集团有限公司航天推进技术研究院,西安710100 [3]航天工程大学宇航与科学技术系,北京101416

出　　处：《航空动力学报》2020年第8期1578-1585,共8页Journal of Aerospace Power

基　　金：装备预研重点实验室基金(6142704190101)。

摘　　要：采用集总燃烧模型对某自燃推进剂模型燃烧室的高频纵向燃烧不稳定性进行了分析,计算了液滴蒸发速率沿轴向分布,忽略化学反应时间,近似采用蒸发速率峰值位置代替集中燃烧锋面位置,采用NASA经验公式给出了相应的敏感时滞和相互作用指数,建立了考虑自燃推进剂液滴蒸发过程的高频纵向燃烧不稳定性量化分析模型。基于系统振荡增益变化曲线,分析了不同液滴初始速度条件下稳定性趋势。研究表明:集中燃烧锋面位置对于高频纵向燃烧振荡具有重要影响,液滴平均粒径和液滴初始速度的增加都会导致其向下游移动,相应振荡增益会减小,稳定性提高。当平均粒径超过150μm时,模型燃烧室振荡增益幅值降低至1.0以下,达到了理论上的稳定。High frequency longitudinal combustion instability of a modeled hypergolic propellants combustor was analyzed through concentrated combustion model, in which the distribution of droplet evaporation rate along flow axis was calculated. The peak position of evaporation rate was used as the position of concentrated combustion front when the chemical time was ignored and the empirical correlation of NASA was used to provide sensitive time and interaction index. Then the model for quantity analysis of high frequency longitudinal combustion instability was built considering the hypergolic propellants droplet evaporation. Based on the curves of system oscillation gain, stability tendency under different conditions of initial droplet radius and injection velocity was analyzed. It showed that the position of concentrated combustion front was critical to high frequency longitudinal combustion instability, improvement of averaged initial droplet radius and velocity could make the front far away from the injection face, and the corresponding oscillation gain could be reduced too, making the system more stable. Especially, when the averaged droplet radius got bigger than 150 μm, oscillation gain of the modeled combustor could be smaller than 1.0 and the combustor could become stable in theory.

关 键 词：自燃推进剂 燃烧不稳定 集总燃烧模型 液滴蒸发 集中燃烧锋面 

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]