Numerical Simulation of Aeroacoustic Phenomena in a Chamber with Backward-facing Step Flow
Flow instabilities and flow-acoustic coupling in the propulsion systems could lead to pressure and thrust oscillations, which reduce the engine performance and could damage the payload. Recently, a large L/D radio tactical solid rocket motor with a backward-facing step in the chamber produced a pressure oscillatory behavior in the hot firing test, which has oscillation frequency coincided with the first longitudinal eigenmode. LES method has been used to simulate the backward step flow to investigate the pressure oscillation and aeroacoustic phenomenon. The result suggests that vortex shedding and impingement cycle under unsteady flow condition driven acoustical oscillations. As earlier analytical and experimental studies, the nozzle cavity plays an important role in the amplification of the sound pressure fluctuations. However, the most important improvement of the motor performance should be focused on changing the backward-facing step configuration to break the flowacoustic coupling and feedback loop.
vortex shedding LES backward-facing step solid rocket moter
ZHANG Xiang-yu HE Guo-qiang LIU Pei-jin
Science and Technology on Combustion, Internal Flow and Thermal-structure Laboratory,Northwestern Polytechnical University, Xian, China
国际会议
4th International Symposium on Jet Propulsion and Power Engineering(第四届喷气推进与动力工程国际会议 ISJPPE2012)
西安
英文
357-364
2012-09-10（万方平台首次上网日期，不代表论文的发表时间）