火箭发动机燃烧室中燃烧噪声的计算模型  

Calculation model of combustion noise in rocket motor chamber

作　　者：曾佳进 李军伟[1] 马宝印 李春杰 王宁飞[1] ZENG Jiajin;LI Junwei;MA Baoyin;LI Chunjie;WANG Ningfei(School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China;Beijing Institute of Electronic System Engineering,Beijing 100074,China)

机构地区：[1]北京理工大学宇航学院,北京100081 [2]北京电子工程总体研究所,北京100074

出　　处：《航空学报》2023年第18期56-69,共14页Acta Aeronautica et Astronautica Sinica

基　　金：省部级项目。

摘　　要：燃烧噪声一般分为直接噪声和间接噪声,推导了喉部壅塞工况下燃烧室中因不稳定释热产生的直接噪声和间接噪声在时域和频域的计算模型,该模型考虑了熵波的耗散和声波的衰减。将存在不稳定释热的燃烧室简化为加热直管进行理论计算。与实验结果相比,直接噪声预示误差小于4%,压力扰动的趋势基本一致。基于该模型分析了管长和温度扰动对噪声强度的影响,结果表明:管长越短,直接噪声和间接噪声强度越大;管长越长,直接噪声和间接噪声分离越清晰;直接噪声和间接噪声强度随温度扰动线性增加,无耗散条件下直接噪声增长率和强度均是间接噪声的2倍。Combustion noise is generally divided into direct noise and indirect noise.The model of direct and indirect noises caused by unstable heat release in combustors with throat congestion is derived in time and frequency domain,respectively.The dissipation of entropy waves and attenuation of acoustic waves are considered.A combustor with unstable heat release is simplified as a straight tube heated by an electric heat source for theoretical calculation.Com⁃pared with the experimental results,the prediction error of the direct noise is smaller than 4%,and the trend of pres⁃sure disturbance is basically the same.Based on this model,the effects of pipe length and temperature disturbance on noise intensity are analyzed.The results show that the shorter pipe length causes larger intensity of direct and indi⁃rect noises,and the longer pipe length results in clearer separation between these two noises.The intensity of the di⁃rect noise and indirect noise increases linearly with the temperature disturbance,and the growth rate and intensity of the direct noise are twice that of the indirect noise without dissipation.

关 键 词：计算模型 熵波 声波 直接噪声 间接噪声 燃烧噪声 火箭发动机燃烧室 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]