Numerical Study On The Influence Of Guide Vane-stator Position On The Aerodynamic Performance Of Sector Cascade

As one of the core components,the improvements on performance of aircraft engines raise high demand on the compressor.In the process of design and development of copressor,cascade experiments occupied an important position.The high difficulty and high cost of stage experiment enhanced the significance of sector cascade experiments.Wake-Leading edge impact,the impact of upstream guide vane wake on downstream stator is an important research direction,understanding the effect of the fan blade is necessary.Meanwhile,compared with the stage experiment,the flow intensity achieved a greater value in sector cascade clearance.The accuracy and credibility of the experiment can be ensured by study and control cascade internal secondary flow,and is of great significance to improve the aerodynamic performance of compressor.A compressor sector cascade combined by the adjustable guide vane(AGV)and the stator is discussed.Through the method of numerical simulation,the relative circumferential position of existing model was modified in order to investigate the impact on the parameters and flow field of stator outlet by vane wake shocking the stator leading edge.The results show that the direct impact between wake and the tip of the stator leading edge should be achieved in order to achieve the least effect on stator flow field.Then the guide vane clearance is set in the cascade which more passages with better periodicity of the outlet flow field obtained by adjusting the relative circumferential position of two blade rows.In order to investigate the clearance flow condition and its impact on AGV flow field,guide vane outlet flow parameters and near-wall-flow is analyzed..The results show that guide vane clearance leakage vortex was imported into the clearance area,and increased the cascade loss.At the same time with the increase of gap height,the influence of clearance flow increased.Finally,under the conditions above,stator with tip clearance were analyzed.Through the method of numerical simulation,the stator flow field under the influence of guide vane leakage flow in different AGV clearance was studied.The results show that the guide vane clearance flow significantly reduced the ability of stator in pressure increasing but the static pressure at stator outlet maintained.At the same time,under the existence of the tip clearance,the process of pressure increase in stator delayed.Stator clearance flow hindered the formation of tip clearance vortex and obviously influenced the near-wall stator wake form.