The　effects　of　the　location　and　geometry　of　the　upstream　slot　on　the　end-wall　film　cooling　performance　of　a　gas　turbine　blade　are　numerically　investigated　by　solving　three-dimensional　Reynolds-Averaged　Navier-Stokes　(RANS)　equations　coupled　with　the　k-ω　turbulence　model.　Based　on　the　accuracy　validation　of　the　numerical　method,　the　effects　of　three　slot　locations　on　the　film　cooling　effectiveness　of　the　end-wall　are　numerically　analyzed.　Three　convergent　trapezoid　slot　models　are　proposed,　and　the　effect　of　these　models　on　the　end-wall　flow　and　cooling　characteristics　are　investigated.　The　results　indicate　that　the　increase　of　the　distance　between　the　slot　and　the　blade　leading　edge　reduced　the　film　cooling　effectiveness　of　the　region　near　the　leading　edge　influenced　by　the　horseshoe　vortex,　but　when　the　mass　flow　ratio　(M)　is　larger　than　1.0%,　the　uniformity　of　the　film　cooling　effectiveness　distribution　is　improved.　When　M=0.5%,　the　slot　locating　at　the　position　0.1　times　axial　chord　away　from　the　blade　leading　edge　resulted　in　the　ingestion　of　mainstream　flow.　Comparing　with　the　nominal　slot,　the　three　convergent　trapezoid　slot　models　improved　the　end-wall　film　cooling　effectiveness　significantly.　Especially　for　M=1.0%,　the　greatest　improvement　of　end-wall　average　film　cooling　effectiveness　is　as　much　as　105.36%　with　the　convergent　trapezoid　slot　models.　Besides,　the　models　prevented　the　ingestion　of　mainstream　flow　when　M=0.5%.　©　2017,　Press　of　Chinese　Journal　of　Aeronautics.　All　right　reserved.