In　order　to　improve　the　performance　of　the　turbine　rotor　blade　squealer　tip,　the　effects　of　the　rib　structure　on　the　vortex　inside　the　tip　clearance　and　the　mechanism　of　reducing　the　heat　transfer　coefficient　and　aerodynamic　loss　are　investigated.　Effects　of　the　rib　layout　on　the　heat　transfer　and　aerodynamic　performance　of　the　turbine　rotor　blade　squealer　tip　were　numerically　investigated　using　the　three-dimensional　Reynolds-Averaged　Navier-Stokes　(RANS)　solution　and　k-ω　turbulence　model.　Based　on　the　GE-E3　turbine　rotor　blade　squealer　tip　structure,　four　kinds　of　rib　layouts　of　full　rib　layout,　half　rib　layout　connected　with　suction　side,　half　rib　layout　connected　with　pressure　side,　and　half　rib　layout　in　the　rear　squealer　cavity　along　the　camber　line　were　designed　in　equal　spacing.　The　numerical　prediction　heat　transfer　coefficient　distribution　was　well　agreement　with　the　experimental　data.　The　accuracy　of　the　numerical　method　and　turbulence　model　was　validated.　The　obtained　results　show　that　the　averaged　heat　transfer　coefficients　of　the　blade　tip　with　the　half　rib　layout　in　the　rear　squealer　cavity　decreases　by　11.3%,　3.1%,　11.3%　and　2.8%　by　comparison　of　the　squealer　tip　without　rib　layout　and　with　full　rib　layout,　half　rib　layout　connected　with　suction　side,　half　rib　layout　connected　with　pressure　side.　The　similar　total　pressure　coefficient　of　the　rotor　blade　with　half　rib　layout　connected　with　pressure　side　and　half　rib　layout　in　the　rear　squealer　cavity　is　obtained.　The　total　pressure　coefficient　of　rotor　blade　with　half　rib　layout　connected　with　pressure　side　and　half　rib　layout　in　the　rear　squealer　cavity　reduces　by　1.4%,　2.7%　and　4.0%　compared　to　the　squealer　tip　without　rib　layout　and　with　full　rib　layout,　half　rib　layout　connected　with　suction　side.　The　rib　layout　can　efficiently　decrease　the　vortex　strength　in　the　squealer　tip　cavity　and　corresponding　aerodynamic　loss.　In　addition,　the　weaker　strength　vortex　in　the　upstream　squealer　tip　cavity　enters　into　the　downstream　cavity　through　the　half　rib　in　the　rear　cavity.　This　flow　behavior　reduces　the　heat　transfer　coefficient　of　the　rear　region　in　the　squealer　tip.　The　squealer　tip　with　the　half　rib　layout　in　the　rear　squealer　cavity　shows　the　best　aerothermal　performance.　©　2020,　Editorial　Department　of　Journal　of　Propulsion　Technology.　All　right　reserved.