阻尼环对固体火箭发动机热声振荡的影响

为了有效解决推进系统中热声压力振荡的危害问题,对热声压力振荡的抑制特性进行系统研究.基于固体火箭发动机设计一种平面火焰圆柱形燃烧室实验装置,根据此实验系统,开展阻尼环及其安装位置对热声压力振荡抑制影响的实验,并通过理论计算对实验规律进行了验证.结果显示:无阻尼环时燃烧室内激发出频率为115 Hz,振幅为119 dB的1...

The Influence of Inhibiter Ring on Thermoacoustic Oscillations in Solid Rocket Motor

The suppression characteristics of thermoacoustic pressure oscillation is systematically investigated to effectively solve the thermoacoustic pressure oscillation in a propulsion system. For solid rocket motors (SRM), an experimental system with a flat flame cylindrical combustion chamber was designed. According to the experimental system, the influences of the inhibiter ring and its installation position in combustion chamber on thermoacoustic pressure oscillation were experimentally studied, and the influence characteristics were verified through theoretical calculation. The results show that a first-order pressure oscillation with a frequency of 115 Hz and an amplitude of 119 dB is excited in the combustion chamber without inhibiter ring. After the inhibiter ring is installed, the amplitude of the first-order pressure oscillation is reduced to 81 dB, which is reduced by about 32%, but at the same time, a weaker high-order pressure oscillation is also excited. As the inhibiter ring moves towards the outlet boundary of combustion chamber, the amplitude of the first-order pressure oscillation is further decreased by 13%, while the amplitude of the high-order pressure oscillation increases slightly. The theoretically calculated results are in good agreement with the experimental results, indicating that the inhibiter ring increases the damping of the system, thereby effectively suppressing the thermoacoustic pressure oscillation. And the inhibiter ring near the outlet boundary has greater damping, and the suppression effect is more obvious.