Numerical Research on Non-axisymmetric End Wall Modeling of 1.5-stage Turbine Blades
In order to investigate the effect of end-wall modeling on the aerodynamic performance and flow field charac-teristics of turbine blades,the effect of non-axisymmetric end-wall modeling on the differential pressure of turbine rotor blades was analyzed,and the theoretical study was carried out based on non-axisymmetric end-wall modeling.A modeling scheme with upper convex and lower concave hub of turbine blades was proposed,and the effect of non-axisymmetric end-wall modeling on the secondary flow loss of turbine flow field was studied.The numerical simulation results show that non-axisymmetric end wall shaping method plays an important role in reducing lateral pressure difference,and the non-axisym-metric end wall shaping at the saddle point of the rotor hub is better than the shaping in the channel.Different interval sha-ping of the lower end wall of the turbine can effectively reduce the secondary flow loss in the turbine lobe channel,and the use of non-axisymmetric end wall shaping method can effectively reduce the total pressure loss coefficient of 0.132 2％at the outlet of the turbine lobe.
turbine bladesnon-axisymmetric endwallmodeling methodtotal pressure loss coefficientflow field char-acteristics
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维普
