The　overall　film　cooling　performance　of　three　novel　film　cooling　holes　has　been　numerically　investigated　in　this　paper,　including　adiabatic　film　cooling　effectiveness,　heat　transfer　coefficients　as　well　as　discharge　coefficients.　The　novel　holes　were　proposed　to　help　cooling　injection　spread　laterally　on　a　cooled　endwall　surface.　Three-dimensional　Reynolds-averaged　Navier-Stokes　(RANS)　equations　with　shear　stress　transport　(SST)　k-x　turbulence　model　were　solved　to　perform　the　simulation　based　on　turbulence　model　validation　by　using　the　relevant　experimental　data.　Additionally,　the　grid　independent　test　was　also　carried　out.　With　a　mainstream　Mach　number　of　0.3,　flow　conditions　applied　in　the　simulation　vary　in　a　wide　range　of　blowing　ratio　from　0.5　to　2.5.　The　coolant-to-mainstream　density　ratio　(DR)　is　fixed　at　1.75,　which　can　be　more　approximate　to　real　typical　gas　turbine　applications.　The　numerical　results　for　the　cylindrical　hole　are　in　good　agreement　with　the　experimental　data.　It　is　found　that　the　flow　structures　and　temperature　distributions　downstream　of　the　cooling　injection　are　significantly　changed　by　shaping　the　cooling　hole　exit.　For　a　low　blowing　ratio　of　0.5,　the　three　novel　shaped　cooling　holes　present　similar　film　cooling　performances　with　the　traditional　cylindrical　hole,　while　with　the　blowing　ratio　increasing,　all　the　three　novel　cooling　holes　perform　better,　of　which　the　bean-shaped　hole　is　considered　to　be　the　best　one　in　terms　of　the　overall　film　cooling　performance.