燃气喷射角度对含硼固体火箭超燃冲压发动机补燃室燃烧效率的影响  

Effect of gas injection angle on combustion efficiency of secondary combustion chamber for solid rocket scramjet containing boron

作　　者：凌江 徐义华[1] 孙海俊[1] 冯喜平[2] LING Jiang;XU Yihua;SUN Haijun;FENG Xiping(Jiangxi Key Laboratory of Micro Aero Engine, School of Aircraft Engineering, Nanchang Aeronautical University, Nanchang 330063, China;Key Laboratory of Combustion, Thermal Structure and Internal Flow Field, Northwestern Polytechnical University, Xi'an 710072,China)

机构地区：[1]南昌航空大学飞行器工程学院江西省微小航空发动机重点实验室,江西南昌330063 [2]西北工业大学燃烧、热结构与内流场重点实验室,陕西西安710072

出　　处：《火箭推进》2022年第1期69-75,89,共8页Journal of Rocket Propulsion

基　　金：国家自然科学基金(51666012)。

摘　　要：固体火箭燃气超燃冲压发动机具有高比冲、结构简单、流量易调节等优点,然而在超音速空气流的补燃室中,如何让燃料更好地与空气掺混,增加颗粒停留时间,在较短时间内释放出更多的燃烧焓成为目前研究的重点。采用Realiazble k-ε湍流模型,单步涡团耗散模型,在King的硼颗粒点火燃烧模型的基础上考虑了硼颗粒在高速气流当中的气动剥离效应,利用龙格-库塔算法迭代计算硼颗粒点火燃烧过程,对燃气进气方向与轴向夹角从45°~180°的10种进气方式下的补燃室进行了三维两相燃烧流动计算,分析了各种进气角下的燃气燃烧效率、硼颗粒燃烧效率以及总燃烧效率。结果表明:当一次燃气喷射角度与轴向夹角逐渐增加时,燃气与颗粒燃烧效率逐渐增加,并在180°时燃烧效率和比冲为最高。Solid rocket gas-fired scramjet has the advantages of high specific impulse,simple structure and easy flow adjustment.However,in the secondary combustion chamber with supersonic air flow,how to make the fuel mixed with air better,increase the residence time of gas and particles,and release more combustion enthalpy in a short time has become the focus of current research.Based on King's ignition and combustion model of boron particles,realiable k-εturbulence model and single-step vortex dissipation model are adopted in this paper,and the aerodynamic stripping effect of boron particles in high-speed airflow is considered.The Runge Kutta algorithm is used to iteratively calculate the ignition and combustion process of boron particles.The three-dimensional two-phase combustion flow in the secondary combustion chamber under 10 intake modes with the angle between gas inlet direction and axial direction from 45°to 180°is calculated.In addition,the gas combustion efficiency under various intake angles,the combustion efficiency of boron particles and the overall combustion efficiency are analyzed.The results show that when the angle between the injection angle of primary gas and the axial angle increases gradually,the combustion efficiency of fuel gas and particles increases gradually,and the combustion efficiency and the specific impulse reach the highest at 180°.

关 键 词：航天推进系统 硼粉 固体火箭 超燃冲压 两相流二次燃烧 

分 类 号：V236[航空宇航科学与技术—航空宇航推进理论与工程]