The Research On Characteristic Performance Of Combustion Flow Field In Secondary Combustion Chamber For Extended Range Solid Rocket Ramjet

Based on related development work of extended range ammunition, the research on performance characteristics of combustion flow field in secondary combustion chamber for extended range solid rocket ramjet was carried out in this dissertation. The combustion flow field in secondary combustion chamber for static and spinning extended solid rocket ramjet were studied experimentally and numerically in detail.Physical and mathematic model of investigating combustion characteristics of secondary combustion chamber for static extended solid rocket ramjet was established. The k-s turbulent model, eddy dissipation model and PDF model were considered in this dissertation, and the interphase coupling model was taken into account in the computation between gas and Al particles. The structural mesh was used in mesh modeling.The combustion two phase flow field in secondary combustion chamber for static extended solid rocket ramjet was simulated numerically with physical model and mathematic studied in this dissertation. Reasonable flow field structure information and the distribution of gas state parameters were obtained. The influence of the particles diameter, particles content, outlet pressure of secondary combustion chamber, inlet air temperature particles adds and the combustion efficiency reduces. With increasing Mg content, it is helpful to improve the combustion efficiency of aluminum particle. Under the same Mg content, the combustion efficiency of aluminum particle reduces with increasing particle diameter.Under the condition of considering additional force on particles produced by rotating, the combustion gas and two phase flow field in secondary combustion chamber for spinning extended solid rocket ramjet were simulated numerically. The Reynolds stress turbulent model was adopted in the computation. The influence of rotation speed on combustion and flow characteristics of solid rocket ramjet was researched on the basis of numerical simulation results.Using the ramjet union experiment system, the internal ballistic test and ramjet union experiment of choked solid rocket ramjet with central air inlet were studied, the ramjet union experiment of unchoked solid rocket ramjet with side air inlet were respectively studied. The pressure and temperature distribution in secondary combustion chamber for solid rocket ramjet were obtained. Numerical result was almost consistent with experimental data that validates the mathematic model and numerical calculation program studied in this dissertation are correct and reliable. It is proved that the solid rocket ramjet can work normally as temperature response curve is consistent with pressure variation curve on time region. of secondary combustion chamber, air-fuel ratio and Mg content on combustion efficiency and the distribution of gas state parameters were analyzed in detail. The results show that it has two diffusion flame peaks at the entrance of secondary combustion chamber which are mixed to one diffusion flame peak in the middle of secondary combustion chamber due to the complexity of solid rocket ramjet studied in this dissertation. With increasing aluminum particle diameter, the combustion efficiency of it decreases and outlet temperature drops too. With increasing air-fuel ratio, the combustion efficiency of aluminum particle decreases. With increasing content, absolute quality of burnedThe combustion and flow characteristics in second combustion chamber of extended solid rocket ramjet and lots of experimental data of performance characteristics for ramjet were acquired through this research. The practice shows that research work is instructive significance for the design and application of ramjet second combustion chamber, and lays a solid foundation of developing deeper research on extended range solid rocket ramjet.