In　this　paper,　conjugate　heat　transfer　numerical　simulations　about　the　combined　impingement/film　cooling　structure　on　the　leading　edge　of　the　GE-E3　first-stage　blade　were　carried　out.　The　standard　k　-　ω　turbulence　model　was　adopted,　and　the　effect　of　film　hole　angle　with　symmetrical　arrangement　on　the　combined　impingement/film　cooling　characteristics　on　the　turbine　blade　leading　edge　were　analyzed;　Under　the　five　coolant　mass　flow　ratios　(MFR=0.005,　0.010,　0.016,　0.020,　0.025),　the　cooling　and　heat　transfer　performance　on　the　turbine　blade　leading　edge　at　different　film　hole　angles　(β=20,　25,　30,　40,　50,　60)　were　studied.　The　results　showed　that:　According　to　studied　cases　in　this　paper,　the　smaller　the　film　hole　angle　is,　the　higher　the　area-averaged　overall　cooling　effectiveness　on　the　turbine　blade　leading　edge　is;　As　the　coolant　mass　flow　ratio　increases,　the　area-averaged　overall　cooling　effectiveness　on　the　turbine　blade　leading　edge　gradually　increases.　©　2021,　Science　Press.　All　right　reserved.