The launch vehicle will experience extreme acoustic environment at lift-off, which will cause the invalidation and destruction of the aerospace equipment, and reducing noise is of great significance for improving launch safety. In this paper, the numerical simulation of gas–liquid two-phase flow and its acoustic field is carried out, and the flow field is simulated by the discrete phase model (DPM), second-order Roe format, Scale-Adaptive Simulation (SAS) and three-dimensional Navier–Stokes. Based on the analysis of the flow field, the acoustic analogy integration method (FW-H) is used to predict the jet noise at the observation position. The influence of the water different injection angles and mass flow rate ratios are studied, and the results show that water injection not only reduces the temperature, velocity and vorticity at the gas–liquid interface, and the temperature at the bottom of the jet deflector, it also significantly reduces the jet noise. The total sound pressure level can be reduced to 6.92 dB by appropriate selection of the water injection angles and water injection mass flow rates. The numerical method established in this paper provides a useful tool for the design and analysis of water injection noise reduction for high-thrust multi-nozzle launch vehicle.

运载火箭在升空时会经历极端的声学环境，导致航天设备失效和毁坏，降低噪声对提高发射安全具有重要意义。本文对气液两相流及其声场进行数值模拟，采用离散相模型（DPM）、二阶Roe格式、尺度自适应模拟（SAS ) 和三维 Navier-Stokes。在流场分析的基础上，采用声类比积分法（FW-H）对观测位置的射流噪声进行预测。研究了不同注水角度和质量流量比的影响，结果表明注水不仅降低了温度，气液界面处的速度和涡量，以及射流偏转器底部的温度，也显着降低了射流噪声。The total sound pressure level can be reduced to 6.92 dB by appropriate selection of the water injection angles and water injection mass flow rates. 本文建立的数值方法为大推力多管运载火箭注水降噪的设计和分析提供了有用的工具。