Solid Rocket Afterburning Indoor Gas Mixing Theory And Experimental Study

To predict the mixing flow-field in the combustion chamber of Solid Rocket Ramjet and provide some directions for engineering development, numerical simulations of the non-reactive mixing flow were made. Models with real scale were build with 3D CAD tool to get result as exactly as possible. And to increase computation efficiency with available hardware resources, each whole model was split into several elementary sub-domains meshed with hexahedron cells but only the most complex sub-domain was meshed with tetrahedron cells. SIMPLE method for compressible flow based on unstructured grid companied with k - s turbulence model was used. Good stability and convergence speed resulted from using jointly SIMPLE method and coupled explicit method with multi-grid.The cold flow field in a model of reduced scale was measured with Phase Doppler Particle Analyzer (PDPA) and the Vanka's cases were computed with the present method again. Both the experiment and the computation were used to estimate the method of this project.In this project, several configurations were simulated. Analysis of the results was made and the characteristic size's influence to mixing was summarized. According to the concept of mixing degree, among those configurations an optimum one was found. These method, result and analysis could be useful for engineering development and numerical simulations of the reactive mixing flow.