The　strong　swirling　flow　and　nonuniform　temperature　at　the　outlet　of　lean　oil　premixed　combustion　chamber　transfer　downstream,　which　directly　affects　the　aerodynamic　performance　of　the　vane　endwall　of　downstream　turbine,　and　then　changes　the　endwall　heat　transfer　and　film　cooling　characteristics.　The　combustion　chamber　is　designed　with　typical　outlet　velocity　and　temperature　characteristics.　Comparing　with　the　experimental　data,　we　have　verified　that　the　swirling　flow　and　temperature　distribution　of　designed　combustion　chamber　outlet　is　typical.　In　this　paper,　we　studied　the　influence　of　combustion　chamber　outlet　swirling　flow　on　the　flow　pattern,　heat　transfer　and　film　cooling　characteristics　of　the　turbine　vane　endwall　by　numerical　solution　of　3D　Reynolds-averaged　Navier-Stokes　(RANS)　equation　and　shear　stress　transport　turbulence　model　(SST　k-ω).　The　flow　field　pattern,　heat　transfer　and　film　cooling　characteristics　of　the　turbine　vane　endwall　at　5　relative　positions　along　the　pitch　between　the　center　of　combustion　chamber　outlet　swirling　flow　and　the　turbine　vane　are　compared　and　analyzed.　The　result　shows　that　when　the　center　of　combustion　chamber　outlet　swirling　flow　is　facing　the　vane　1,　the　lateral　movement　of　the　pressure　side　leg　of　the　horseshoe　vortex　is　weakened,　and　the　heat　transfer　at　endwall　exacerbates　due　to　downstream　movement　of　stagnation　point;　the　coolant　at　the　third　row　of　film　hole　is　taken　away　from　the　endwall,　so　the　heat　insulation　effectiveness　of　air　film　decreases.　When　the　swirling　flow　center　is　facing　the　vane　2,　the　pressure　side　leg　of　the　horseshoe　vortex　envelopes　the　coolant　at　the　second　row　of　film　hole　and　impacts　suction　surface,　which　improves　the　secondary　cooling　effect　while　the　average　film　cooling　effectiveness　at　the　endwall　surface　increases　(the　maximum　value　is　0.148,　and　the　surface　averaged　net　heat　flux　reduction　is　0.055　5).　This　study　reveals　the　influence　mechanism　of　the　combustion　chamber　outlet　swirling　flow　on　the　flow　field　pattern,　heat　transfer　and　film　cooling　characteristics　at　the　endwall　of　the　downstream　turbine　vane,　which　provides　some　reference　for　the　layout　design　of　endwall　film　cooling.　©　2022,　Editorial　Office　of　Journal　of　Xi＇an　Jiaotong　University.　All　right　reserved.