Abstract: Experimental study on combustor temperature field of heavy-duty gas turbine(E) was finished on high-pressure test system.Experimental results indicate that: circular temperature distribution coefficient of combustor is 0.2538,and radial temperature distribution coefficient is 0.1312,all of which do not meet the design requirements.Through adjustment of mix-holes size and layout of chamber,and increase of the penetration depth and intensity of mixing,the circular temperature distribution coefficient decreased to 0.2164,radial temperature distribution coefficient decreased to 0.0897,approaching the design target.The results have important significance for the experiment of similar combustors.