Experimental and Numerical Investigation on Pressure Oscillation Induced by Flow Instability in SRM
- Paper number
IAC-09.C4.P.9
- Author
Mr. Xiaolong Chen, China
- Coauthor
Prof. Guoqiang He, Northwestern Polytechnical University, China
- Coauthor
Prof. Peijin Liu, China
- Year
2009
- Abstract
Pressure oscillation in solid rocket motors, which has been a continuing problem, is believed to have a great relationship with the coupling between flow instability induced by vortex shedding and acoustics of combustion chamber. Vortex shedding could be divided into three categories including obstacle, surface and corner vortex shedding. A large amount of experimental and numerical study has been done on the former two categories by many researchers. We designed a rectangular cold-gas experimental facility to study corner vortex shedding in finocyl grain solid rocket motor. The cold gas was injected axially into the experimental facility with the handy air-supplier in our laboratory. Pressure is measured by Dytran 2300V1. The mean flow velocity is changed by moving the throat pintle along longitudinal direction. Pressure-time curves show that large pressure oscillation occurs in the experimental facility when the throat pintle moves to a special position. The frequency from FFT process of experimental data matches well with the first longitudinal acoustic mode of experimental facility which was tested using a sound speaker and an acoustic transducer. Analysis of these experimental data indicates that, for a motor with given geometry, a range of mean flow velocity exists when large pressure oscillation occurs. Large eddy simulations of flow-acoustic coupling in cold-gas experimental facility were done after the validation of theory methodology by computing the cold-gas motor of VKI. The numerical results agree well with the experimental data. In conclusion, the flow-acoustic coupling in solid rocket motors is validated experimentally and numerically in this paper.
- Abstract document
- Manuscript document
IAC-09.C4.P.9.pdf (🔒 authorized access only).
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