Numerical study of combustion characteristics of secondary combustion chamber with cavity under dual intake structure
In response to the problem of mixed combustion in the solid ramjet secondary combustion chamber of missile application,the temperature field and flow field distributions of the secondary combustion chambers with cavity(with a caster angle range of 90°-150°)under dual 90° and dual 180° intake conditions are investigated using a gas-phase combustion model of primary gas and a KING combustion model of boron fuel.The cavity swirl effect and its impact on combustion process and combustion products are elaborated.Quantitative analysis of combustion performance is conducted.The numerical results show that the cavity increases the mixing space of fuel and air under the dual 180° intake condition,and four large opposing vortices appear on the cavity cross-section,making the mixing more uniform and conducive to the combustion organization,the effective combustion space is larger,and the total combustion efficiency at the outlet of the secondary combustion chamber reaches 85％.Under the dual 90° intake condition,a counterclockwise unidirectional vortex is formed on the cavity cross-section,and the combustion is concentrated in a narrow space,which is unfavorable for the combustion process,and the total combustion efficiency at the outlet of the secondary combustion chamber is only 55％.When the caster angle of cavity increases from 90° to 120°,the fuel-air mixing space is increased,which promotes the combustion process.As the caster angle of cavity continuously increases to 150°,the effect of increasing the cavity space on improving combustion is weak.
dual intake structurecavitysecondary combustion chamberboron particlescombustion process
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