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Experimental investigation on effects of injection distribution on combustion instability in a model rocket combustor
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NSTL
Self-excited combustion instabilities of transverse modes were experimentally investigated in a rectangular multi-injector model combustor, operating with the bipropellants O_2/CH_4. The propellants were injected through a linear array of five oxidizer-centered shear coaxial injectors into the combustor. High-amplitude limit cycles obtained in hot-fire tests were analyzed in detail. Different combustion instability modes, including first and second width modes, were observed in cases with three different injection distribution schemes. Hence, the injection distribution strongly determined the combustion dynamics. One insight can be gained that the stable combustion could be achieved by properly designing the propellants' injection distributions.
transverseexperimentallyrectangular
Lei Ni、Yongjie Ren、Wei Lin、Yiheng Tong、Wansheng Nie、Kangkang Guo
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Department of Aerospace Science and Technology, Space Engineering University, Huairou 101416, Beijing, China
NSTL
