Numerical　investigations　on　the　aerodynamic　and　cooling　characteristics　of　the　Turbine　vane　endwall　with　micro-ribbed　structure　were　conducted　by　using　the　three-dimensional　ReynoldsAveraged　Navier-Stokes(RANS)　and　SST　k　-ω　turbulent　model　based　on　ANSYS-CFX.　The　accuracy　of　the　utilized　numerical　approach　was　validated　by　comparing　the　cooling　effectiveness　using　CFD　predictions　and　the　experimental　data.　The　effects　of　the　designed　micro-ribbed　endwall　and　the　mass　flow　rate　of　the　upstream　slot　coolant　jet　were　investigated　using　numerical　approaches.　The　numerical　results　show　that　the　interaction　between　the　pressure　side　endwall　secondary　flow　and　coolant　jet　can　be　decreased　significantly　by　introducing　the　micro-ribbed　endwall　along　the　pressure　side.　Furthermore,　the　coolant　jet　moves　along　the　ribs　towards　the　downstream　direction　with　little　influence　of　the　lateral　flow.　Consequently,　the　cooling　effectiveness　along　the　pressure　side　endwall　is　increased　remarkably　with　the　introduction　of　the　micro-ribbed　endwall.　In　addition,　the　endwall　secondary　flow　is　reduced　by　the　micro-ribbed　endwall,　hence　the　micro-ribbed　endwall　leads　to　a　lower　level　of　aerodynamic　loss.　©　2019,　Science　Press.　All　right　reserved.