Effect　of　turbine　inlet　swirl　condition　(swirl　intensity　and　orientation)　on　endwall　heat　transfer　performance　with　combustor-turbine　misalignment　at　transonic　condition　was　numerically　investigated,　and　coolant　injection　from　combustor-turbine　interface　was　also　considered.　Simulations　with　two　mainstream　swirl　numbers　(SN)　of　0.6　and　1.0,　two　swirl　orientations,　two　endwall　misalignment　modes　and　slot　coolant　injection　were　conducted　by　solving　the　three-dimensional　RANS　equations　coupled　with　the　Reynolds　Stress　Turbulence　Model　(RSM).　Computational　results　indicate　that　for　anticlockwise　swirled　condition,　the　averaged　Nu　number　of　the　high　heat　transfer　attachment　region　upstream　of　the　leading　edge　decreases　from　4400　to　3100　with　the　increasing　SN　from　0.6　to　1.0.　Negative　incidence　is　caused　at　hub　followed　by　a　low　heat　transfer　region　at　pressure　side　junction.　Enhanced　horseshoe　vortex　and　mainstream　direct　attachment　enlarge　the　hot　ring　(uncooled　area　around　the　vane　leading　edge)　when　SN　=　0.6.　As　for　clockwise　swirled　condition,　positive　incidence　is　caused　at　hub　and　can　have　some　effect　on　reducing　the　passage　crossflow.　The　pressure　side　low　heat　transfer　region　enlarges　under　aligned　mode　but　shrinks　under　misaligned　mode　compared　with　anticlockwise　condition.　Averaged　Nu　distributes　more　uniformly　along　axial　direction.　The　hot　ring　can　only　be　observed　when　SN　=　0.6　under　misaligned　condition.　For　aligned　mode,　endwall　heat　transfer　at　x/Cax　©　2019　Elsevier　Ltd