自燃推进剂直流互击式喷嘴高压燃烧试验  

High pressure combustion experiment for hypergolic propellant unlike doublet injectors

作　　者：张锋 孙毅 尚帅 杨宝娥 ZHANG Feng;SUN Yi;SHANG Shuai;YANG Baoe(National Key Laboratory of Aerospace Liquid Propulsion,Xi'an Aerospace Propulsion Institute,Xi'an 710100,China)

机构地区：[1]西安航天动力研究所航天液体动力全国重点实验室,西安710100

出　　处：《航空学报》2024年第11期288-296,共9页Acta Aeronautica et Astronautica Sinica

基　　金：国家级项目。

摘　　要：为指导高室压液体姿轨控发动机推力室喷注器设计,采用铬青铜热沉燃烧室开展了四氧化二氮/一甲基肼(NTO/MMH)直流互击式喷嘴高压燃烧试验研究,获得了混合比、孔径比、鲁泊数、撞击角、燃烧室压力等参数对特征速度和燃烧效率的影响规律。试验结果表明,随着混合比、孔径比、鲁泊数或撞击角的增大,实际特征速度和燃烧效率均呈现出先增大再基本保持不变最后减小的趋势;随着燃烧室压力的提高,实际特征速度和燃烧效率先明显增大后基本保持不变。当混合比在1.71~2.31、孔径比在1.2~1.4、鲁泊数在0.68~1.28、撞击角在70°~80°及燃烧室压力高于3 MPa时,燃烧效率可达0.97~0.98的较高水平。To guide the design of thrust chamber injectors for high chamber pressure orbits and attitude control rocket engines,we conduct combustion tests of NTO/MMH unlike doublet injectors at high pressure using the chrome bronze heat sink combustor.The effects of the mixing ratio,ratio of injection orifice diameter,Rupe number,impinging angle and chamber pressure on the characteristic velocity and combustion efficiency are obtained.The results show that,increase in the mixing ratio,ratio of injection orifice diameter,Rupe number or impinging angle leads to initial increase,then constant,and final decrease in the characteristic velocity and combustion efficiency.With the increase of the chamber pressure,the characteristic velocity and combustion efficiency first increase significantly and then remain unchanged.A mixing ratio between 1.71 and 2.31,injection orifice diameter 1.2 and 1.4,Rupe number 0.68 and 1.28,impinging angle 70°and 80°,and chamber pressure over 3 MPa indicate a high combustion efficiency level of 0.97-0.98.

关 键 词：姿轨控发动机 直流互击式喷嘴 自燃推进剂 燃烧 鲁泊数 燃烧效率 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]