中小推力火箭发动机试车降噪方案仿真分析  

Simulation analysis on noise reduction schemes for smalland medium thrust rocket engine testing

作　　者：孙得川 黄欣寅 王园丁 郭曼丽 邵青 SUN Dechuan;HUANG Xinyin;WANG Yuanding;GUO Manli;SHAO Qing(State Key Laboratory of Structural Analysis,Optimization and CAE Software for Industrial Equipment,Dalian University of Technology,Dalian 116024,China;Shanghai Institute of Space Propulsion,Shanghai 201112,China)

机构地区：[1]大连理工大学工业装备结构分析优化与CAE软件全国重点实验室,辽宁大连116024 [2]上海空间推进研究所,上海201112

出　　处：《火箭推进》2024年第2期27-38,共12页Journal of Rocket Propulsion

基　　金：国防科技工业局支持项目。

摘　　要：火箭发动机试车时的噪声很大,降低其强度对于环境保护很重要。针对中、小推力液体火箭发动机试车,提出了引射筒、消声器及喷水组合的降噪方案,并进行了数值仿真研究。结果表明:引射筒不仅起引射作用,而且将主要的喷流噪声源区域与环境隔离,在降噪中起主要作用;对于小推力发动机喷流,格栅型消声器的降噪效果很好,不必附加喷水措施;对于中等推力发动机喷流,喷水的降噪作用不明显,其主要作用是降温和减小燃气扩散污染,不宜采用过大的喷水量和过小的喷雾粒径;对于300 N级发动机,引射筒承载的力较小,而后部的隔声墙会承载与推力相当的力,对于3 kN级发动机,引射筒会承载发动机的大部分推力,后部的隔声墙会承载较小的力。The noise generated during rocket engine testing is very large,and reducing its intensity is important to environmental protection.A noise reduction scheme was proposed for the testing of medium-and small-thrust liquid rocket engines,which included an ejector tube,muffler,and water spray combination,and numerical simulation research was conducted.Research has shown that the ejector not only serves as an ejector but also isolates the main jet noise source area from the environment,playing a major role in noise reduction.For small-thrust engine jets,the noise reduction effect of grid-type silencers is very good,and there is no need to add water spraying measures.For medium-thrust engine jets,the noise reduction effect of water spray is not obvious,and its main role is to cool down and reduce gas diffusion pollution.It is not suitable to use too large water spray flow and too small spray particle size.For 300 N level engines,the ejector tube carries less force,while the rear wall carries a force equivalent to the thrust.For 3 kN level engines,the ejector tube carries most of the engine’s thrust,while the rear wall carries less force.

关 键 词：火箭发动机 试车 气动噪声 降噪 数值模拟 

分 类 号：V411.6[航空宇航科学与技术—航空宇航推进理论与工程]