Application of a Time-Marching Based Throughflow Model in Transonic Axial Compressor

摘要：

A throughflow model based on the time-marching finite volume approach is described in this paper. The governing equations are derived by circumferentially averaging the three-dimensional Navier-Stokes equations neglecting the circumferentially non-uniform and viscous terms. An inviscid blade force model similar to the Large-particle method is derived. The viscous blade force has been modeled by the distributed loss model. The convective fluxes of the governing equation are discretized with the Edwards low-diffusion flux-splitting (LDFSS) scheme. And a point-iterative Symmetric Gauss-Seidel (SGS) scheme is used in the temporal discretization. The throughflow model has been applied to the NASA Rotor 67 and a high-load transonic fan stage ATS-2. The reasonable good agreements with the experiments and the 3D viscous computations show the potential of the method.

关键词： throughflow model time marching transonic axial compressor

作者: H.L.Jin X.J.Li X.M.Gui

作者单位: Aeroengine Numerical Simulation Research Center Beijing University of Aeronautics and Astronautics B The College of Engineering Peking University Beijing, China School of Jet Propulsion Beijing University of Aeronautics and Astronautics Beijing, China

会议类型: 国际会议

会议名称: The 3rd International Symposium on Jet Propulsion and Power Engineering(第三届喷气推进与动力工程国际会议 ISJPPE)

会议地点: 南京

会议语种:英文

页码: 74-81

在线出版日期: 2010-09-13（万方平台首次上网日期，不代表论文的发表时间）