In　order　to　develop　high　efficiency　cooling　method　for　the　leading　edge　of　gas　turbine　blade,　a　conjugate　heat　transfer　study　on　the　impingement-film　composite　cooling　structure　of　the　first　stage　blade　leading　edge　of　GE-E3　gas　turbine　is　carried　out　with　standard　k-ω　turbulence　model.　Effects　of　the　impingement-film　composite　cooling　and　swirl-film　composite　cooling　on　the　turbine　blade　leading　edge　composite　cooling　characteristics　are　compared　and　analyzed.　Firstly,　the　performance　of　five　turbulence　models　(standard　k-Ε　model,　RNG　k-Ε　model,　standard　k-w　model,　SST　k-w　model,　SST　k-w　γ-Reθ　transition　model)　in　the　prediction　of　impingement　and　film　composite　cooling　is　validated　with　experimental　data.　Then　the　grid　independence　is　verified.　Finally,　the　comprehensive　cooling　efficiency,　the　flow　field　structure　and　the　internal　temperature　distribution　inside　the　blade　leading　edge　materials　are　compared　and　analyzed　in　detail　under　the　conditions　of　the　two　cooling　schemes.　And　the　effects　of　coolant　to　mainstream　mass　flow　ratio　and　film　hole　spanwise　angle　on　the　combined　cooling　performance　of　blade　leading　edge　of　the　impingement-film　composite　cooling　and　the　swirl-film　composite　cooling　are　studied.　The　results　show　that　within　the　scope　of　the　study,　the　overall　average　cooling　efficiency　of　the　swirl-film　composite　cooling　is　6%　higher　than　that　of　the　impingement-film　composite　cooling　for　any　coolant　mass　flow　ratio　and　film　hole　structure.　In　the　study　range,　the　averaged　overall　cooling　efficiency　of　the　leading　edge　for　the　both　cooling　schemes　increases　as　the　coolant　mass　flow　ratio　increases,　while　the　temperature　of　the　blade　leading　edge　material　decreases.　©　2021,　Editorial　Office　of　Journal　of　Xi＇an　Jiaotong　University.　All　right　reserved.