The　numerical　investigation　on　shaped　trench　film　cooling　was　carried　out　using　Reynolds　averaged　Navier-Stokes　simulation　to　test　its　practical　utility.　The　cooling　performance　of　three　kinds　of　film　holes　(standard　cylindrical　film　holes,　transverse　trenched　and　segmented　trenched　film　holes)　on　a　flat　plate　was　studied　firstly　to　verify　the　numerical　method　and　illustrate　the　vortex　structures　in　detail.　Then　the　cooling　characteristics　of　the　three　kinds　of　film　holes,　which　are　located　at　five　single　row　positions　around　a　turbine　vane,　were　compared　in　operating　conditions.　The　parameters　of　adiabatic　film　cooling　effectiveness,　discharge　coefficient　and　total　pressure　losses　are　analyzed　with　the　blowing　ratios　from　0.5　to　3.0,　and　the　optimal　position　on　turbine　vanes　for　the　novel　trenched　film　hole　was　confirmed.　The　results　show　that　the　trenched　cooling　holes　produces　more　uniform　coolant　distribution　laterally　at　all　positions,　leading　to　higher　cooling　performance　particularly　at　high　blowing　ratios.　The　unique　vortex　configuration　generated　by　segmented　trench　shows　clear　advantages　at　the　small　curvature　positions　on　the　pressure　side,　where　the　mainstream　influence　is　minimum　and　is　more　suitable　for　the　novel　structure.　The　flow　resistances　in　trenched　film　holes　are　less　than　that　in　cylindrical　holes.　The　magnitude　of　the　total　pressure　losses　of　the　three　cooling　holes　are　almost　the　same.