摘要
针对抗性消声器中扩张结构和尾管引起的射流噪声问题,建立了低马赫数射流噪声有限元分析模型。基于双方程k-ε紊流模型理论对射流速度场进行了计算,发现喷射流的势核周围形成一段湍化程度极高的气流。采用Lighthill-Curle声学理论预测了射流噪声,并通过试验对比验证了模型和数值计算方法的正确性。研究表明,喷射噪声主要集中在势核周围,说明势核是引起射流噪声的主要原因。通过对指向性的研究表明,低马赫数射流最大噪声主要分布范围为15°~60°。
Aimed at the jet noise which is induced by the expand structure and tail tube in the resistant muffler,a finite element model at low Mach number was developed.Based on the theory of double-equation k-ε turbulent model,the velocity field induced by the jet was calculated and it was found that there was a turbulent flow around the flow core.The jet noise was predicted by using Lighthill-Curle acoustic theory.The model and the numerical calculation method was proved to be correct by comparing with the experiment.The result shows that jet noise is mainly induced by the flow core.The jet noise directivity was also researched and the result indicate that at low Mach number,the maximum noise mainly occurs in the range of 15°～60°.
出处
《内燃机工程》
EI
CAS
CSCD
北大核心
2009年第2期34-38,共5页
Chinese Internal Combustion Engine Engineering
基金
重庆市自然科学基金资助项目(CSTC,2006BA7013)
关键词
内燃机
低马赫数
射流噪声
计算气体声学
指向性
IC engine
low Mach number
jet noise
computational aero-acoustics
directivity
