Influence of two air inlets on combustion efficiency of fuel-rich flow field laden with boron particle
- Paper number
IAC-06-C4.P.2.01
- Author
Mr. Lu Xiang, Northwestern Polytechnical University, China
- Coauthor
Prof. Guoqiang He, Northwestern Polytechnical University, China
- Coauthor
Prof. Pei-Jing Liu, Northwestern Polytechnical University, China
- Coauthor
Mr. Qin Fei, Northwestern Polytechnical University, China
- Year
2006
- Abstract
Adopting secondary air inlets for solid rocket ramjet, a better performance can be achieved, enhancing the ignition of boron particles and combustion efficiency. Numerical studies on the two-phase reacting flow field of solid rocket ramjet with secondary air inlets were carried out, concerning the fly condition of Mach 3.0. Using k-e turbulence, one-step eddy-dissipation model was adopted for gas phase, while stochastic tracking model was taken for the effect of instantaneous turbulent velocity fluctuations on the particle trajectories. Focusing on the influence of air inlets distance and air mass flow rate ratio on the combustion efficiency of both gas phase and discrete phase, eight configurations are examined to cover a representative range of solid rocket ramjet with secondary air inlets. An understanding for the combustion efficiency promotion of solid rocket ramjet with secondary air inlets was achieved, deducing several equations for assessing the influence of air inlets distance and air mass flow rate ratio, drawing several conclusions from the results. It shows that a proper air inlets distance and air mass flow rate ratio exists which brings an optimal combustion efficiency for both gas phase and boron particles; air mass flow rate ratio has a major impact on combustion efficiency, which should be the primary design parameter; both factors raise various influence on combustion efficiency, a much more complex model should be established to evaluate the performance of solid rocket ramjet with secondary air inlets.
- Abstract document