关键词: 冲压火箭发动机;反应流;流动分布;数值仿真

Abstract: A solution algorithm based on coupled solution of the fully elliptic three dimensional steady state Navier Stokes equations was developed for the calculation of turbulent reacting flows occured in ducted rockets.The governing partial differential equations were discretized by finite volumes and the nonlinear algebraic equations were solved by a block implicit algorithm.Turbulence was represented by the k ε model and chemical reaction was assumed to occur in one step at an infinite rate,controlled by mixing of fuel and oxidant streams.It is demonstrated that the strategy of coupled solution is rapidly convergent even in the presence of significant density variations.Calculations with grids as large as 39×13×18 have been made successfully in modest computer time.The combustion efficiency calculated is in good agreement with experimental data

Key words: Ducted rocket engine;Reacting flow;Flow distribution;Numerical simulation