燃料预喷注与释热对高马赫数进气道性能影响的数值研究  

Numerical simulation of fuel pre-injection and heat release effects on higher Mach inlet performance

作　　者：渠镇铭 李海涛 罗飞腾 陈文娟 QU Zhenming;LI Haitao;LUO Feiteng;CHEN Wenjuan(School of Aerospace Engineering,Huazhong University of Science and Technology,Wuhan 430074,China)

机构地区：[1]华中科技大学航空航天学院,湖北武汉430074

出　　处：《推进技术》2024年第7期33-47,共15页Journal of Propulsion Technology

摘　　要：为掌握高马赫数条件下燃料预喷注与释热对进气道性能的影响,以来流马赫数Ma_(∞)=10为设计点进行了典型二元构型进气道设计与基准流场仿真,开展了Ma_(∞)=7~10进气道氢燃料预喷注、反应流场仿真研究。结果表明:预喷注引起局部压缩激波系变化、改变下游流动特性、从而影响进气道性能,主要会导致总压恢复系数、喉部马赫数减小;同时预喷注动作具有一定的激波系调节、压缩循环调控的作用,且与预喷注位置密切相关,外压缩喷注会诱导外部斜激波向亚额定偏移,导致流量溢流增加、流量系数减小;内压缩喷注可以避免流量溢流,对进气道性能影响相对较小,且双侧组合喷注的预混效率可达0.60以上。反应流场仿真显示,燃烧反应主要发生在近壁面区域,流向上主要释热区在内压缩段,反应释热进一步降低总压恢复系数、减小喉部马赫数,外压缩喷注时会增加流量溢流,而循环静压比、静温比均相对增大,阻力系数基本保持不变,整体上预喷注及释热影响效应具有可控性。In order to understand the effects of fuel pre-injection and heat releases on the performance char-acteristics of high Mach scramjet inlet,a typical inlet with Ma_(∞)=10 design-point was designed and finished the simulation of the benchmark inlet flowfield.Moreover,hydrogen-fueled pre-injection and reaction flowfield simu-lations were conducted during flight Ma_(∞)=7~10 conditions.The results show that the pre-injection can induce the change of local compression shock wave system,alter downstream flow characteristics,and thus affect the inlet performance,mainly resulting in the decrease of total pressure recovery coefficient and throat Mach number;si-multaneously,the pre-injection action has a certain effect in adjusting the shock wave system and compressing cycle regulation and is closely related to the pre-injection position.Specifically,the external pre-injection will induce the external oblique shock wave to shift towards the sub-rated state,increasing the flow spillage and decreasing the flow coefficient.The internal pre-injection can avoid flow spillage,with relatively small effects on the performance of the inlet.The premixing efficiency of the combined injection on both sides can reach above 0.60.In addition,the reaction flowfield shows that combustion reactions occur in the near-wall regions and the main heat release in the internal compression section,which further decreases total pressure recovery coefficient and throat Mach number.In contrast,the cycle static pressure ratio and static temperature ratio all relatively increased.The drag coefficient remains unchanged,the flow spillage will further increase with external compression injection.Overall,the pre-injection and heat release effects are controllable.

关 键 词：高马赫数超燃发动机 高超声速进气道 进气道预喷注 释热效应 激波调整 数值模拟 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]