超声速轴对称进气道噪声环境及其影响因素研究  

Study on aero-acoustics of an axial-symmetric supersonic inlet and its influencing factors

作　　者：高庆[1,2] 李会娜[3] 陈新民[2] 赵永辉[1] 

机构地区：[1]南京航空航天大学机械结构力学及控制国家重点实验室,南京210016 [2]中国运载火箭技术研究院,北京100076 [3]北京强度环境研究所,北京100076

出　　处：《应用力学学报》2018年第2期384-390,共7页Chinese Journal of Applied Mechanics

基　　金：国家重点实验室2015年开放课题(MCMS-0115G01);国防技术基础科研项目(JSZL2015203B002)

摘　　要：针对某典型轴对称超声速进气道的噪声环境,利用全尺寸和缩比模型,研究分析了飞行马赫数、攻角、堵塞度、模型缩比、发动机工作状态等参数对进气道气动噪声环境的影响,辨识确定了进气道壁面脉动压力系数的变化规律和主要影响因素,并与传统弹体外表面的脉动压力系数变化规律及影响因素进行了对比分析。研究结果表明:攻角变化的影响较小,发动机工作状态对进气道噪声有一定贡献;对于较小的堵塞度,压缩区脉动压力系数基本不受来流马赫数影响,扩张段随来流马赫数的增大而增大;脉动压力系数随堵塞度的增大而逐渐增大,当达到一定条件时(在25%~50%之间),进气道内产生显著的空腔共鸣,导致脉动压力系数急剧增大;且噪声量级较大时,缩比模型和全尺寸的测量结果存在明显差异,缩比模型的测量结果偏大6dB左右。A study on aero-acoustics characteristics of a supersonic inlet and influencing factors is presented. This study is conducted on a representative axial-symmetric inlet and its scaled model. Most influencing factors are studied, such as Mach number, the angle of attack, blockage factor, engine rating and scaled ratio. It is demonstrated that wall-pressure fluctuations coefficients are almost not influenced by the angle of attack, in certain degree by engine rating. With smaller blockage factor, the coefficients are almost not influenced by Mach number in compression zones, but increase in the expansion zone. The coefficients increase with blockage factors,and suddenly at a certain blockage factor(between 25% and 50% ), while the cavity resonance occurs. At high level, there is distinguished a deviation between scaled and full scale, measurements on scaled model are higher around 6 dB.

关 键 词：进气道噪声 轴对称超声速进气道 壁面脉动压力系数 影响因素分析 

分 类 号：V216.5[航空宇航科学与技术—航空宇航推进理论与工程]