关键词: 航空发动机;跨音速压气机;轴流风扇;纳维尔－斯托克斯方程;数值计算

Abstract: A code to solve three dimensional Navier Stokes equation has been developed,which has been used to predict the flow field of a transonic,low aspect ratio and axial flow fan rotor.The code was based on an explicit,time marching and finite volume method.The independent variables of equations were stored at the corners of contorl volume.Turbulence was modeled by Baldwin Lomax eddy viscosity model.Two step Runge Kutta method was implemented to solve the algebraic equations.Some accelerating convergence techniques such as multi grid and local time step method were employed.Performance maps at design rotationg speed were calculated by the code.The emphasis of the paper is on the calculation of flow field at choked point,near stall point and at peak efficiency point.Comparation of predicted data with experimental result illustrates that the code can simulate a transonic,low aspect ratio and axial flow fan rotor

Key words: Aircraft engine;Transonic compressor;Axial flow fan;Navier Stokes equation;Numerical calculation