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The influence of the squealer rim thickness on the tip leakage flow and heat transfer characteristics of the gas turbine blade was numerical investigated using Reynolds-Averaged Navier-Stokes (RANS) solutions and k-ω turbulent model.The linear experimental blade with a flat tip was used to validate the numerical prediction results.The obtained results of the heat transfer performance with different squealer rim thickness were well agreement with experimental data.Five squealer rim thickness from 1.00mm to 2.50mm was utilized to analyze the tip leakage flow and heat transfer characteristics of the blade tip.The complex flow structure in the squealer tip was observed compared with the flat tip.The numerical results show that the increased thickness of the squealer rim reduced the leakage flow rate into the groove.The effects of the leakage flow impinge into the groove become weak.The location of high heat transfer coefficient on the groove bottom moved to the leading edge and the area was smaller due to the less leakage gas and flow reattachment moving to the leading edge.