Spinning effect on the flow of exhaust gas in combustion chamber of a solid rocket motor

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作者：
Department of Aerospace Engineering, Harbin Engineering University, Harbin 150001, China [1 ]
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来源：
Kongqi Donglixue Xuebao | 2008年 / 2卷 / 208-211+245期
关键词：
Solid propellants - Combustion chambers - Flow fields - Rockets;
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摘要：
The RNG k-Ε turbulent model is adopted to calculate the united flow field in a rocket motor with cannular solid propellant in the condition of different rotating speeds. The characteristic of exhaust gas in the chamber, the tangential velocity distribution of the swirling gas and the change of swirl core size are obtained. The flow field configuration close-by front seal in the chamber is also analysed particularly.
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