Abstract: Supersonic secondary combustion of fuel rich gases, enhanced by air injection was experimentally investigated. Numerical solutions of the finite volume discretized full Navier Stokes equations were obtained for the experimental flow fields with chemical reaction flow. Lower Upper decomposition scheme and MUSCL type approach were used. A chemical reaction model with 12 species and 16 elementary reactions was presented to describe the supersonic combustion. The chemical source term was treated by the use of a point implicit method. Compared with experimental data, the simulation results are reasonable and reliable.

Key words: Ducted rocket engine;Supersonic combustion;Afterburning;Combustion test;Numerical simulation

摘要： 利用富燃料固体推进剂燃烧产生的高温燃气与侧喷空气混合进行了超声速补燃实验。运用有限体积法求解轴对称N S方程和组分方程,对实验流场进行了数值模拟,计算中采用了LU时间隐式格式、MUSCL空间离散方法、12组分16反应的化学反应模型,对化学反应源项进行了点隐式处理。结果表明:实验方法可行,计算结果合理、可靠。

关键词: 冲压火箭发动机;超声速燃烧;加力燃烧;燃烧试验;数值模拟