On burnout performance of a rocket-engine-based incinerator devised for high burning rate of solid particles

A rocket-engine-based incinerator is proposed as a compact device of a solid-particle incinerator for high-performance burnout of wastes with solid phase. Burnout performance is investigated numerically in the chamber devised for this purpose. The present chamber employs design concepts of swirl flow and nozzle shape applied to a furnace of power-plants and a rocket combustor, respectively. As the first step, non-reactive flow field is analyzed in the incinerator with primary injectors and secondary injectors through which coal fuel and air are supplied. Deflection angle of a primary injector, incline angle of a secondary injector, gap between two-type injectors are selected as design parameters. Swirl number is adopted for evaluation of the degree of swirl flow and it is estimated over wide ranges of three parameters. Swirl number varies non-monotonically depending on the combination of the parameters. Burnout ratio increases with swirl number. High swirl number is attained over broad ranges of deflection and incline angles. From the numerical results, the design points with high burning performance can be found by maximizing swirl number. The proposed chamber has been verified to attain higher burnout performance than a conventional incinerator by a factor of 10.