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The real turbine inlet boundary conditions have significant spatial nonuniformity,which has a strong effect on downstream aerodynamic characteristics.However,the importance of the total pressure nonuniformity in publications is less considered.This article deals with the influence rule and the mechanism of different inlet total pressure distributions on the aerodynamic losses of aero turbines.Total pressure distortion height and maximum total pressure distortion intensity at the exit of the combustion chamber were used to structure modeled different nonuniform inlet boundary conditions that imposed on the nozzle guide vane and the first stage of the GE-E3 highpressure turbine.The results show that when the total pressure near the endwall is higher than the total pressure in the midspan,the increase of the total pressure intensity at endwall or the increase of the distortion height will significantly reduce the aerodynamic efficiency of the turbine.The convergence and collision of the flow near the pressure surface mainly caused this phenomenon.When the total pressure near the endwall is weaker than the total pressure in the midspan,the different non-uniform features have no obvious effect on total aerodynamic losses.