双气路内并联进气系统模态转换试验研究  

Experimental Study on Mode Transition Course of Inner Over/Under Inlet System with Double Flow Path

作　　者：母忠强 杨顺华 王铁军[2] 任虎[2] 游进[1] 谢松柏 张弯洲 罗佳茂 Mu Zhongaqiang;Yang Shunhua;Wang Tiejun;Ren Hu;You Jin;Xie Songbai;Zhang Wanzhou;Luo Jiamao(Beijing Aerohydrodynamic Frontier Research Center,Beijing 100029,China;Science and Technology on Scramjet Laboratory of CARDC,Mianyang 621000,China)

机构地区：[1]北京流体动力科学研究中心,北京100029 [2]中国空气动力研究与发展中心、高超声速冲压发动机国防科技重点实验室,四川绵阳621000

出　　处：《气动研究与试验》2024年第3期69-80,共12页Aerodynamic Research & Experiment

摘　　要：为了探究内并联进气系统模态转换过程中的分流板调节策略,利用地面试验研究方法,研究了Ma 3.5条件下双气路进气系统在典型分流板位置的流场干涉机制,获得了高低速气路总体性能和流场变化规律。研究结果表明,分流板高度变化影响高低速气路总体性能和抗反压能力,同时由于流量重新分配,下游动力系统的工作状态需要匹配调节;分流板调节对高速气路性能影响更显著,随着高速气路逐渐关闭,受激波强度变化影响,高速气路总压恢复系数会经历迅速下降再缓慢上升的过程;当出口反压比超过临界值,激波系会在分流板前缘和唇口之间以低频大振幅和高频小振幅相结合的方式往复运动,该非定常效应导致流场和总体性能不稳定,模态转换过程中应避免该情况发生。To explore splitter adjustment tactic of double flow path inlet system while the mode transition course with fixed free stream Mach number,by using the method of ground test,the variation rules of total performance and flow field on the typical splitter height has been obtained.The results show that the change of splitter height affects the total performance and resistance of back pressure,and it also leads to the redistributing of mass flow rate,which means that the operation of engine downstream should match the regulation;the splitter adjustment affects the total performance of high speed flow path more remarkable,and because of the change of shock wave intensity as the high speed flow path closes,the total pressure recovery coefficient of high speed flow path decreases first and then increases slowly;when the outlet pressure ratio overpass the critical value,the shock wave is a back and forth movement between cowl lip and splitterleading edge in the form of low frequency with high amplitude and high frequency with low amplitude,and the unsteady effect leads to the instability of flow field and total performance,which should be avoided during mode transition course.

关 键 词：组合发动机 双气路进气系统 模态转换 分流板 地面试验系统 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]