Research On Numerical Simulation For Integrated Flow Field Of Supersonic Inlet And Combustor

The solid rocket ramjet, which combines the techniques of ramjet propulsion and solid rocket propulsion, offers the following advantages for missile propulsion: high specific impulse, simple configuration, high credibility, convenient using and high maneuverability. So it becomes the first choice for the propulsion system of supersonic tactics missiles. As the air-breathing engine, the performance of solid rocket ramjet is determined not only by structure of engine and the performance of propellant, but also by flight condition. For studying the performance of solid rocket ramjet under the influence of different flight conditions, it's significant to simulate the integrated flow field of inlet and combustor.The structure design and the performance research of supersonic inlet/combustor are key techniques for solid rocket ramjet. The performance of supersonic inlet determines the pressure and the air flux in combustor, then affect the work of ramjet. This thesis is aimed at the pilot study about the integrated flow field of inlet and combustor, which is based on the optimized design and the performance analysis of supersonic inlet, in order to provide theoretical basis and direction for extension of flight enveloping and improvement of the synthetic performance of ramjet.In this paper, two-dimensional and three-dimensional flow models in supersonic inlet and a simple reacting flow model in combustor and integrated flow field are established on the basis of k ?εtwo-equation turbulence model and Steady-Compressible N-S equations, which are dispersed by finite volume method. With enough numerical simulation, some significant results are listed below: a) For optimized design of inlet which works in a large range of mach number, the low intensity of expand waves can weaken the intersection and the reflection of oblique shock in inlet mouse and expand waves, which improves the whole performance. b) With the theoretical analysis and fitting experimental data, the performance prediction model of inlet is established. c) There is a difference between the numerical simulation results of two-dimensional and three-dimensional flow field in supersonic inlet, which shows the influence of boundary layer on the side wall. d) In the three-dimensional flow field of supersonic inlet, boundary layer on the side wall brings about the corner vortex which locates on right-angle site of the channel section. So the final normal shock becomes a set of compression waves because of the flow separation induced by corner vortex, and the second throat appears, which declines the total pressure resume coefficient and strengthens...