Abstract: This study focuses on the squealer tip film cooling design of turbine blades, presenting three layouts: two with full ribs, one with a full rib and a half-rib on the pressure side, and one with a half-rib on the suction side. Using numerical simulations through three-dimensional Reynolds-Averaged Navier-Stokes（RANS） equations and a standard k-ω turbulence model, the heat transfer and cooling performance of grooved blade tips with two full rib layouts were studied under four different blowing ratios.The aerodynamic and heat transfer performance, as well as film cooling effectiveness of blade squealer tip with different rib layouts and typical squealer tip without rib layout were compared and analyzed at blow ratio 1.0 condition. Results show that the distribution of heat transfer coefficient at the blade tip predicted by numerical methods is in good agreement with the experimental measurement results, which verifies the reliability of the numerical method; at a blowing ratio of 1.0, the squealer tip with full ribs exhibits the highest average film cooling effectiveness, surpassing the typical groove design by 2.2% in effectiveness. The layout with half ribs on the pressure side shows the lowest average heat transfer coefficient and total pressure loss. Rib configurations markedly alters the flow structure over the leaf top, thereby affecting its aerothermal performance and film cooling effectiveness, with the full rib layout displaying optimal overall aerothermal performance and cooling effectiveness.