超燃发动机燃烧室三维化学反应流场的数值模拟

3 D NUMERICAL SIMULATION OF SUPERSONIC REACTING FLOWS IN SCRAMJET COMBUSTOR

采用ＬＵ隐式方法强耦合求解有限体积法离散的完全Ｎ－Ｓ方程及组份方程，数值模拟超燃发动机燃烧室内的化学反应流场。计算中采用了ＡＵＳＭ通量分裂格式，两方程及八方程的化学反应模型。计算得到了流场的结构与组份分布，并对两种化学反应模型的结果进行了比较与分析。

A three dimensional numerical code has been developed to simulate supersonic reacting flows in scramjet combustor. The code employs a finite volume, lower upper(LU) splitting implicit time marching method to solve the compressible Navier Stokes and species equations in a fully coupled manner. An upwind flux split method named AUSM is adopted . A two step global and an eight step hydrogen air chemistry model are used to simulate the combustion of hydrogen and air. A combustor model with parallel injections has been studied. The pressure, temperature contour as well as the mass fraction distribution of the species are presented. The performance of the two chemistry models are discussed. The eight step model shows superiority to the two step model.