三维非定常进气畸变快速数值模拟程序

摘要AbstractFor the evaluation of stability of aero-engine,a major limiting factor of compressorinstability is inlet distortion.Long length scale unsteadiness such as that caused by low orderinlet distortion in all aero engine have a significant influence in engine performance andstability.The stall margin,pressure ratio and efficiency can be considerably reduced inoperating environments for which the inlet conditions are ken-uniform.So,it very importantto emphasize the research of effect of compressor performance and stability response to inletdistortion.This paper presents a computational model for describing complex three-dimensionalnon-linear disturbances associated with inlet distortion of the flow through the full annulus incompressors.The difficulty problem to solve inlet distortion flow field is treat with the flow inducts and intra-blade-row gaps which is described by the three-dimensional unsteady Eulerequations for mass,momentum,and energy conservation with source terms of body force.Small structures of blade row passage scale of flow passing through the filter will besimulated via body force models.Large scales above a certain threshold are directlycalculated from the governing equations of the flow.Adequate numerically simulation ofthese phenomena by suing this computational model only requires smaller computer resourcesthan current three-dimensional CFD of Navier-Stokes equation with appropriate turbulencemodels,they will be in the reach of the designer wishing to perform such calculations on aroutine basis.In this paper,our computational results of compressor response to total pressure inletdistortions have been verified experimentally at a wider range of different operation speed ofa fan rotor.The predictions of the model for mass flow,pressure ratio and efficiency of thisfan in operating environments of inlet total pressure distortions are in agreement withexperimental data.In addition,this model some predictions of performance response and flowstructure to inlet temperature distortions,inlet pulsant total pressure and inlet temperaturepulse.The model predictions satisfy current empirical,numerical or analytical sources.Theserepresent a advantage in the predictions of the inlet distortions.Keywords:fan/compressor,inlet distortions,circumferential average body force model,three-dimensional unsteady flowii