固体火箭发动机燃气射流噪声数值模拟

Numerical Simulation for Gas Jet Noise of Solid Rocket Engine

摘要:

为了研究固体火箭发动机燃气的气动噪声特性,建立了二维轴对称的射流数学模型,采用大涡模拟(LES)方法对火箭发动机超声速燃气射流流场进行了数值模拟,然后利用 FW-H 面积分得到了超声速燃气射流噪声的分布特性。 计算结果表明:该方法能较好地捕捉超声速燃气射流的复杂波系流场结构,射流噪声辐射具有较明显的指向性。

Abstract:

In order to investigate the aerodynamic noise characteristics of solid rocket engine’s gas, a two-dimensional axi- symmetric mathematical model is established. Large eddy simulation (LES) is applied to simulate the supersonic gas jet flow field of rocket engine. The distribution characteristic of supersonic gas jet noise is obtained based on FW-H surface integral. The calcula- tion results show that the method can capture the flow field structure of complex wave system of supersonic gas jet flow, and the jet noise radiation has obvious directivity.