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.