Abstract: In order to better predict the characteristics of the turbine stage non-constant flow and analyse the influence of inlet temperature aberration on the downstream lobe discharge.Taking a single stage high pressure turbine as the research object,the distribution conditions of total inlet temperature are changed,and the influence of inlet temperature distortion on Mach number,blade heat load and other factors,as well as the change law of high-temperature air migration path are designed under three schemes:uniform inlet temperature distribution,radial non-uniform inlet temperature distribution and hot spots at turbine inlet.The results show that the inlet temperature aberration has little effect on the internal flow field of the single-stage turbine,the radial uneven distribution of the inlet temperature will lead to the appearance of a band-shaped high temperature region in the middle and upper part of the radial direction of the guide vane,and the highest temperature is found in the leading edge of the guide vane at the high point of 60%of the vane,and this phenomenon will be aggravated by the existence of the hot streak,and the inlet temperature aberration will not cause a large-scale change of the highest temperature value of the surface of the guide vane in the same cycle.The main stream gas is accelerated by an elliptical heat spot in the turbine flow path.As the mainstream gas accelerates in the turbine flow path,the heat spot gradually Narrows from elliptical shape and the temperature decreases.After the trailing edge of the guide blade interacts with the shedding vortex,the squeezed edge of the gas presents a zigzag shape.After the static and dynamic interface surface,the heat load is more significant at the leading edge of the moving blade and the pressure surface of the moving blade.The inlet temperature distortion will not cause the high temperature air flow to deviate greatly in the radial direction.