Numerical Simulation of flow field and radiation of an aluminized solid-propellant rocket multiphase exhaust plume

摘要

The aluminum oxide (A12O3) liquid or solid particle radiation is significant in the plume radiation of an aluminized solid-propellant rocket motor. This paper has researched the influences of A12O3 particles size and initial velocity at the burning surface in chamber on the exhaust plume flow field and radiation, as well as the Mach number of the missile. Numerical simulation has been done to learn inner and outer integrative two-phase flow field and flow field parameters distribution of gaseous components and AI2O3 particles in many situations have been obtained, compared and analyzed. Structured grid generated by TTM method has been employed. The two-phase flow field was solved by discrete particle model, where the PSIC (Particle Source in Cell) method was employed. The Rosin-Rammler algorithm was used for particle diameter distribution. Then spectral radiance of two dimension axial symmetry plume has been computed by developed model of infrared radiation of solid rocket exhaust plume, and compared with that in document. The study shows that the radiation of particles plays the main roal in the infrared radiation of exhaust plume. The quicker the missile is, the weaker the gaseous radiation is, however, the stronger the solid radiation is. For the same particle dimension, the quicker the burning surface particles are, the weaker the gaseous radiation is, however, the stronger the solid radiation is, and the more particle dimension is, the bigger the influence of particle velocity on plume radiation is. Examination of the gaseous molecular spectra shows that there are three spectral peaks at 1.9-2.2|j.m, 2.7-2.8(4.m and 4.3-4.66(im. In addition, their intensities are related to particle dimension and velocity, as well as solid radiation. It indicates the method of this paper is feasible and the solution is proper.