抽吸位置对固冲发动机进气道性能的影响  

Effect of suction position on inlet performance of solid rocket ramjet

作　　者：牛雨鹏 武志文[1] 张智慧 陈鹏鑫 张伊乔 张旭 NIU Yupeng;WU Zhiwen;ZHANG Zhihui;CHEN Pengxin;ZHANG Yiqiao;ZHANG Xu(School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China)

机构地区：[1]北京理工大学宇航学院,北京100081

出　　处：《航空动力学报》2024年第8期214-225,共12页Journal of Aerospace Power

摘　　要：对于设计马赫数为3的固冲发动机,用二维数值模拟的方法研究了一次燃气流量可调,即背压变化的范围较大的进气道,在不同位置设置抽吸孔对进气道不起动马赫数、抗反压能力以及总压恢复系数的影响。在内压缩段设置抽吸孔使进气道的不起动马赫数由2.7降低为2.4,抗反压能力提高了12.28%;外压缩段抽吸使进气道的不起动马赫数由2.7降为2.6,抗反压能力没有提高;而喉道段抽吸的进气道抗反压能力提高了11.24%,不起动马赫数没有变化。内压缩段和喉道段抽吸可以在一定工况下提高总压恢复,尤其是喉道段抽吸可以提高超额定工况下的总压恢复系数。最后提出了一种提高进气道在马赫数为3~5工况下运行的性能提升方案,在马赫数为4~5工况下总压恢复平均提高了5%左右。For a solid rocket ramjet with design Mach number of 3,two-dimensional numerical simulation was used to study the effects of suction holes at different locations on the unstart Mach number,anti-back pressure capability and total pressure recovery coefficient of an inlet with adjustable primary gas flow,i.e.a large range of back pressure changes.By setting suction holes in the inner compression section,the unstart Mach number of the inlet was reduced from 2.7 to 2.4,and the anti-back pressure capability was increased by 12.28%;The unstart Mach number of the inlet decreased from 2.7 to 2.6 due to the suction of the outer compression section,and the anti-back pressure capability was not improved;however,the anti-back pressure capability of throat suction inlet was increased by 11.24%,and the unstart Mach number did not change.The internal compression section and throat section suction can improve the total pressure recovery under certain working conditions,especially the total pressure recovery coefficient under over rated working conditions.Finally,a scheme to improve the performance of the inlet under Mach number of 3—5 was proposed,and the total pressure recovery under Mach number of 4—5 was increased by about 5% on average.

关 键 词：固冲发动机进气道 抽吸位置 起动特性 抗反压能力 性能提升 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程]