含铝金属化浆体推进剂火箭发动机燃烧性能试验研究 *

推进技术 ›› 2018, Vol. 39 ›› Issue (7): 1650-1659.

含铝金属化浆体推进剂火箭发动机燃烧性能试验研究 *

邵昂¹,朱韶华¹,鄂秀天凤²,潘伦²,邹吉军²,徐旭¹

北京航空航天大学宇航学院，北京 100191,北京航空航天大学宇航学院，北京 100191,天津大学化工学院，先进燃料与化学推进剂教育部重点实验室，天津化学化工协同创新中心，天津 300072,天津大学化工学院，先进燃料与化学推进剂教育部重点实验室，天津化学化工协同创新中心，天津 300072,天津大学化工学院，先进燃料与化学推进剂教育部重点实验室，天津化学化工协同创新中心，天津 300072,北京航空航天大学宇航学院，北京 100191

发布日期:2021-08-15
作者简介:邵昂，男，硕士生，研究领域为液体火箭发动机试验与仿真。 E-mail: jspzcz@126.com 通讯作者:徐旭，男，博士，教授，研究领域为液体 /固体火箭发动机技术。

Experimental Studyon Combustion Characteristic of Rocket Engine Basedon Slurry Propellant Containing Aluminum Particles

School of Astronautics，Beijing University of Aeronautics and Astronautics，Beijing 100191，China,School of Astronautics，Beijing University of Aeronautics and Astronautics，Beijing 100191，China,Key Laboratory of Advanced Fuel and Chemical Propellant of Ministry of Education，School of Chemical Engineering and Technology，Tianjin University，Collaborative Innovative Center of Chemical Science and Engineering Tianjin ，Tianjin 300072，China,Key Laboratory of Advanced Fuel and Chemical Propellant of Ministry of Education，School of Chemical Engineering and Technology，Tianjin University，Collaborative Innovative Center of Chemical Science and Engineering Tianjin ，Tianjin 300072，China,Key Laboratory of Advanced Fuel and Chemical Propellant of Ministry of Education，School of Chemical Engineering and Technology，Tianjin University，Collaborative Innovative Center of Chemical Science and Engineering Tianjin ，Tianjin 300072，China and School of Astronautics，Beijing University of Aeronautics and Astronautics，Beijing 100191，China

Published:2021-08-15

摘要/Abstract

摘要： 为研究含铝浆体推进剂的燃烧特性，对浆体推进剂模型火箭发动机开展了一系列试验研究。分别将质量分数为 21%的纳米铝粉颗粒以及质量分数为 12%的氢化铝复合粒子加入到 JP-10燃料中，对比分析了浆体燃料与纯净燃料在燃烧性能方面的差异。燃烧试验的氧燃比为 1.6～2.0。试验结果表明:与纯净 JP-10燃料相比，加入金属颗粒的 JP-10浆体燃料在雾化和燃烧过程中产生了严重的结块聚集效应，导致其燃烧效率与质量比冲明显降低，而由于浆体燃料密度远大于纯净 JP-10燃料，含纳米铝颗粒的浆体燃料的密度比冲相比于纯净 JP-10燃料有大幅提高，提高幅度为 5.5%～14.6%。试验还发现浆体燃料的点火延迟略低于纯净 JP-10燃料，金属颗粒的加入对推进剂点火性能有积极的影响。试验中采集了喷管出口的固体燃烧产物并进行了 XRD，EDS，SEM，TEM等多种手段分析，发现浆体燃料中铝的氧化率约为 64%～74%，颗粒团聚现象明显，主要呈球形，尺寸分布不均，约为 500nm～3μm。

关键词: 浆体推进剂；燃烧性能；火箭发动机；试验研究；铝粉颗粒

Abstract: A series of model rocket engine combustion experiments were conducted in order to investigatethe combustion characteristics of slurry propellant containing aluminum particles. The fuels used were traditionalliquid JP-10，JP-10-based slurry with 21-wt% loadings of nano-sized aluminum particles and JP-10-basedslurry with 12-wt% loadings of micro-sized aluminum hydride composite particles. The differences in the com.bustion characteristic between the slurry and the pure fuel were analyzed. The oxygen-to-fuel ratios were set tobe 1.6～2.0. The results showed that compared with pure JP-10，the JP-10-based slurries presented obviously lower mass specific impulse and combustion efficiency，due to the special aggregation phenomenon of metal parti.cles in the process of atomization and combustion. However，the JP-10-based slurries achieved a higher density specific impulse by 5.5% to 14.6% compared to pure JP-10，because the metalized propellant has higher density.It was also found that the ignition delay of the slurry fuels was slightly shorter than that of the pure JP-10 fuel and it proved that the addition of metal particles has a positive effect on the propellant ignition performance. In addi.tion，condensed combustion products are sampled in the jet plume behind the exit nozzles to analyze the compo.nents of products. By means of the energy dispersive spectrometer(EDS)，X-ray diffraction(XRD)，scanning electron microscope(SEM)，and transmission electron microscope(TEM)，it was found that 64%～74% alumi. num was oxidized in the tests，and the solid particles are mainly spherical and in size of 500nm～3mm.

Key words: Slurry fuels； Combustion characteristic； Rocket engine； Experimental study； Aluminum particle

邵昂,朱韶华,鄂秀天凤,潘伦,邹吉军,徐旭. 含铝金属化浆体推进剂火箭发动机燃烧性能试验研究 *[J]. 推进技术, 2018, 39(7): 1650-1659.

SHAO Ang¹,ZHU Shao-hua¹,E Xiu-tian-feng²,PAN Lun²,ZOU Ji-jun²,XU Xu¹. Experimental Studyon Combustion Characteristic of Rocket Engine Basedon Slurry Propellant Containing Aluminum Particles[J]. Journal of Propulsion Technology, 2018, 39(7): 1650-1659.

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