Numerical investigation on the combustion characteristics of powder fuel under different regulation parameters

Abstract

A comprehensive numerical study is undertaken to investigate the operating feature in a powder fueled scramjet combustor. The effect of regulation parameters on the flow field and combustion mechanism is examined systematically. The numerical simulation method is developed for multi-species gas-solid two-phase turbulent combustion in the Euler-Lagrange frame. The particle surface reaction model and the Eddy-dissipation Concept model are utilized for powder fuel combustion. The combustor flow field, flame structure, and species distribution in the powder fueled scramjet combustor are revealed in detail. The numerical simulation results show that the combustion organization scheme of tandem double-cavity can provide an excellent flame stabilization effect. The powder fuel achieves continuous combustion and sufficient release heat in the supersonic airflow. The combustion flow field features and flame distribution are strongly influenced by the transport solid-gas ratio and the equivalent ratio. The increase of both regulation parameters improves the combustion efficiency of powder fuel in the region from the injection hole to the downstream cavity. Nevertheless, the large equivalent ratio significantly leads to higher total pressure losses in the combustor.