Abstract: Numerical simulations were conducted to study 3D mixing flow field of the normal fuel injection from different orifice An implicit finite volume method was used to solve the compressible Navier Stokes equations

Key words: Supersonic combustion;Fuel injection;Jet mixing flow;Numerical simulation

摘要： 采用隐式有限体积法求解可压NS方程及组分方程,对超燃发动机内的垂直燃料喷射的三维混合流场进行了数值研究。计算结果表明,采用小角度的楔形喷口,可以基本消除喷口上游的分离区,而且其燃料贯穿性能更好。

关键词: 超音速燃烧;燃料喷射;喷射混合流;数值仿真