Numerical research on the performance of solid fuel rocket scramjet combustor

Abstract

Combustion efficiency is the main factor affecting the performance of solid fuel rocket scramjet. To reveal the influence of combustor configuration on performance and further improve combustion efficiency, the influence of the width-height ratio of the rectangle-section combustor on the performance of solid fuel rocket scramjet is investigated numerically in this article. Three-dimensional compressible Reynolds-averaged Navier-Stokes equations coupled with shear stress transport k– ω turbulence model are employed to simulate the aerodynamics. The Euler–Lagrange approach is used to calculate the multiphase flow. Combustion of carbon particles is modeled by the improved Moving Flame Front model. Accuracy of the present numerical model is validated by the experimental data of a rectangle-section combustor from literature. Results show that as the width-height ratio increases, the combustion efficiency increases first and then decreases. The influence of cavity and its position on the performance are also investigated. Results show that cavity can significantly improve combustion efficiency. The effect of cavity position on performance is related to the distribution of particles.

Experimental Investigation of Solid Rocket Scramjet Based on Central Strut

“…Liu et al [23] attempted a new combustion organization scheme combining cavity and pneumatic slope to enhance the combustion efficiency of a boron-containing propellant solid rocket scramjet, and the combustion performance has proved to be optimized via the enlarged low-speed area near the cavity and the strengthened particles reflux. Huang et al [24] investigated the influence of the cavity and its position on the performance; results show that the cavity can significantly improve combustion efficiency, and the effect of the cavity location on performance is related to particle distribution. Yang et al [25,26] proposed a modular solid scramjet combustor with a Symmetrical Structure and improved the mixing and combustion of the fuel-rich mixture by the narrow/lobe cavity.…”