Influence Of Distorted Flow Field On Aerodynamic Performance Of Compressor Stator Blade Based On Sector Cascade

With the development of shipping and the requirement of environmental protection,the shipping industry’s demand for high power and low pollution is increasing,Gas turbine is playing an increasingly important role in the field of shipping transportation because of its advantages such as small weight size,high power density and quick start.The compressor is one of the core components of gas turbine,its performance and stability directly affect the performance of gas turbine.The particularity of modern shipborne the gas turbine intake system structure makes the phenomenon of compressor inlet distortion more common,especially when the ship sailing encountered crosswinds and storms,resulting in gas turbine intake distortion.Therefore,it is necessary to study the performance and stability of the compressor under the intake distortion,and then explore the method to improve the anti-distortion ability of the compressor.In order to research the flow field of compressor cascade aerodynamic characteristics,this article adopts the method of combining experiment and numerical simulation,with adjustable guide vanes of the sector cascade experiment as an object,the inlet flow field direction is conduces by adjusting the guide blade installation angle.Then analyze the distortion of the stator field as well as the influence of distorted flow field on stator flow field.At last,the non-axisymmetric stators is used to improve the distorted flow field and aerodynamic performance of stators.In this thesis,the aerodynamic parameters of the guide vane outlet at different Mach numbers are studied experimentally,and the flow field changes in guide vane are analyzed by numerical simulation.Finally,the feasibility of creating inlet distortion flow field of stator vane by adjusting No.8 adjustable guide vane is proved to be feasible.Then,different distortion indexes are analyzed.Finally,the outlet flow angle is selected as the main index of inlet distortion of stator vane,and the cause and mechanism of inlet distortion of stator after guide vane rotation are.This thesis studies the distortion of stators under the condition of the internal flow characteristics.Combined with numerical simulation,the influence of the distorted inlet generated by rotating No.8 guide vane on the Mach number,flow angle and total pressure recovery coefficient in the stator passage is analyzed in detail,and the influence of the distorted inlet on the flow state of stator passages is obtained.Finally,this paper designs the No.8 stator blade which is seriously affected by the distorted flow field,the modification of the distorted flow field by non-axisymmetric stator.The research shows that the impact angle of incoming flow at the leading edge of No.8 stator root is reduced at different mach numbers,the total loss of No.8 stators suction surface is reduced and the loss of passage vortex under No.8 stator suction surface is reduced,and the flow structure near No.8 stator is significantly improved.