To　reduce　the　overall　thermal　load　at　squealer　tip　and　improve　the　film　cooling　effectiveness　in　high　heat　transfer　areas,　the　influence　of　pressure-side　coolant　jet　flow　on　heat　transfer　and　film　cooling　performance　of　squealer　tip　in　a　turbine　stage　was　investigated.　The　heat　transfer　coefficient　and　film　cooling　effectiveness　at　squealer　tip　with　two　kinds　of　cooling　hole　shapes　(i.e.cylindrical　and　fan-shaped　holes)　and　five　different　jet　ejection　angles　(20°-40°)　for　pressure-side　cooling　holes　were　obtained　through　numerical　simulations.　The　results　show　that　the　pressure-side　cooling　flow　enters　the　cavity　near　the　leading　edge,　improving　the　cooling　effect　on　the　cavity　floor.　The　pressure-side　coolant　from　the　middle　chord　and　near　the　trailing　edge　holes　forms　the　cooling　film　on　the　tip　surface　and　at　the　tip　trailing　edge,　which　enhances　the　cooling　performance　in　the　tip＇s　high　thermal　load　area.　In　the　present　study,　the　cooling　effect　on　squealer　tip　is　increased　with　the　decrease　of　ejection　angle.　For　the　fan-shaped　holes　at　squealer　tip,　the　area-averaged　heat　transfer　coefficient　is　increased　by　6%　and　the　area-averaged　film　cooling　effectiveness　is　decreased　by　14.3%　on　the　squealer　rim,　whereas　the　area-averaged　heat　transfer　coefficient　is　increased　by　36%　and　the　area-averaged　film　cooling　effectiveness　is　decreased　by　37.2%　in　the　tip　pressure-side　region,　as　the　jet　ejection　angle　increases　from　20°　to　40°.　With　small　jet　ejection　angle,　the　film　cooling　effect　on　the　squealer　tip　and　pressure-side　surface　for　the　fan-shaped　holes　is　better　than　that　of　cylindrical　holes.　If　the　jet　ejection　angle　is　fixed　at　20°,　the　fan-shaped　holes　are　able　to　decrease　the　heat　transfer　coefficient　by　2%　while　increase　the　film　cooling　effectiveness　by　5.9%　on　the　tip　surface,　and　decrease　the　heat　transfer　coefficient　by　22.6%　while　increase　the　film　cooling　effectiveness　by　43.3%　on　the　pressure-side　surface,　as　compared　with　the　cylindrical　holes.　©　2022,　Editorial　Office　of　Journal　of　Xi＇an　Jiaotong　University.　All　right　reserved.