后向台阶-楔体结构对含硼固体火箭超燃冲压发动机燃烧性能影响  

Effect of Step-wedge Structure on Combustion Efficiency of Boron-containing Solid Rocket Scramjet

作　　者：卢国庆 徐义华[1] 胥凯晖[2] 刘炜根 孙海俊[1] LU Guo-qing;XU Yi-hua;XU Kai-hui;LIU Wei-gen;SUN Hai-jun(Engineering Research Center of Aero-engine Technology for General Aviation(Ministry of Education),Nanchang Hangkong University,Nanchang 330063,China;Group 94829 of PLA,Nanchang 330201,China)

机构地区：[1]南昌航空大学通航涡轮动力技术教育部工程研究中心,南昌330063 [2]中国人民解放军94829部队,南昌330201

出　　处：《南昌航空大学学报（自然科学版）》2024年第1期1-9,31,共10页Journal of Nanchang Hangkong University(Natural Sciences)

基　　金：国家自然科学基金(51666012)。

摘　　要：为增强含硼固体火箭超燃冲压发动机中空气与燃气掺混,提升火焰稳定性及燃烧效率,在一次燃气侧向进气基础上,补燃室前段增加后向台阶-楔体组合结构,采用数值模拟的方法分析一次燃气进气方式及楔体结构对含硼固体火箭超燃冲压发动机补燃室内燃烧性能的影响。结果表明:当补燃室结构不变时,一次燃气进气位置到后向台阶的距离从0.5d变化到6d时,硼颗粒燃烧效率先增大后减小,在一次燃气进气位置距台阶为1.25d时,硼颗粒燃烧效率最大,为48%;当一次燃气进气角度在45o~170o内时,一次燃气进气角度越大,发动机燃烧效率越高,一次燃气进气角度为170o时总燃烧效率最大,为71.32%;在一次燃气进气方式不变时,取楔体高度与台阶高度之比分别为0.40、0.50、0.55、0.60、0.65、0.70、0.75、1.00,随着比值增大,总压恢复系数减小,硼颗粒燃烧效率先增大后减小,当楔体高度与台阶高度之比为0.60时,硼颗粒燃烧效率最大,为53.2%。To enhance the mixing of air and combustion gas in the boron-containing solid rocket scramjet and improve the flame stability and combustion efficiency,a backward step-wedge structure was added to the front section of the afterburning chamber based on the lateral intake of primary gas.The impact of the primary gas intake and wedge structure on the combustion performance of the afterburning chamber of the boron-containing solid rocket scramjet were assessed by numerical simulation.The results show that with a constant afterburning chamber structure,changing the distance between the primary inlet position and the step from 0.5d to 6d leads to an initial increase and subsequent decrease in the combustion efficiency of boron particles.At the distance of 1.25d,the combustion efficiency of boron particles peaks at 48%.And the combustion efficiency increases as the primary gas intake angle changes from 45ºto 170º.When the inlet angle is 170º,the total combustion efficiency reaches its maximum,which is 71.32%.When maintaining the primary gas intake mode while tuning the ratio of wedge height to step height as 0.40,0.50,0.55,0.60,0.65,0.70,0.75,1.00 in sequence,the total pressure recovery coefficient decreases as the ratio increases,and the combustion efficiency of boron particles shows an initial rise and a followed decrease,with a peak efficiency of 53.2%achieved at 0.60.

关 键 词：固体火箭冲压发动机 硼颗粒 进气方式 楔体 数值研究 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]