Increasing　turbine　inlet　gas　temperature　is　a　main　approach　to　meet　the　demands　for　high　efficiency　and　thrust　of　advanced　gas　turbine　engines.　Both　of　internal　and　film　cooling　are　often　used　at　the　same　time　for　the　turbine　blade＇s　cooling　to　enhance　the　overall　cooling　performance　and　ensure　the　blade　temperature　below　to　the　heat　resistance　temperature　of　blade　material.　Most　of　open　studies　focused　on　the　individual　cooling　effect　of　either　internal　cooling　or　film　cooling　under　normal　temperature　conditions.　However,　the　actual　working　conditions　of　blade　cooling　is　that　internal　cooling　and　film　cooling　affect　each　other　because　of　the　coolant　flow　through　film　hole　and　the　heat　conduction　inside　the　blade　solid　regions　(including　the　internal　disturbing　elements).　In　addition,　the　temperature　difference　between　turbine　inlet　gas　and　coolant　is　much　high.　It　is　found　that　there　are　few　studies　on　the　coupled　heat　transfer　characteristics　of　turbine　blade　cooling.　To　establish　a　numerical　method　for　coupled　heat　transfer　analysis　of　the　turbine　blade　cooling,　the　coupled　heat　transfer　in　two　perpendicular　channels　which　are　connected　by　a　dividing　wall　and　a　film　hole　through　the　dividing　wall　is　numerically　investigated　by　simultaneously　solving　the　air　flow　and　convective　heat　transfer　equations　in　the　two　passages.　The　heat　conduction　through　the　dividing　wall　(including　the　ribs　equipped　in　the　internal　channel)　and　the　flow　through　the　film　hole　are　also　taken　into　consideration.　The　interaction　between　internal　and　film　cooling　can　thus　be　explored.　The　mainstream　inlet　temperature　is　set　to　be　709　K　to　consider　a　medium　temperature　condition　of　turbine　blade,　and　Reynolds　number　is　1.08　×　105.　The　large-eddy　simulation　(LES)　and　SST　κ-ω　are　employed　to　verify　the　applicability　of　turbulence　models　for　the　simultaneous　simulation　of　internal　and　film　cooling　by　comparing　the　numerical　consequence　with　experiment　from　the　published　literature.　It　is　indicated　that　LES　can　capture　the　fine　structure　of　the　flow　field　and　has　high　accuracy　in　predicting　the　cooling　effect.　It　is　discovered　that　the　heat　conduction　through　the　dividing　wall　of　the　two　channels　increases　both　of　the　internal　convective　cooling　and　the　film　cooling　of　the　mainstream　channel　in　comparison　to　the　adiabatic　cooling　effect　without　considering　the　heat　conduction　inside　the　solid　regions.　In　addition,　the　outflow　through　the　film　hole　improves　Nusselt　number　of　internal　channel,　and　the　ribs　bring　about　a　slight　increase　of　overall　cooling　effectiveness　near　the　behind　zone　of　the　film　hole,　but　decrease　in　the　downstream　a　little　far　from　the　film　hole.　Besides,　adjusting　the　blowing　ratio　could　achieve　higher　blade　cooling　performance.　It　is　suggested　that　we　should　not　stay　in　the　stage　of　studying　internal　or　film　cooling　separately,　but　carry　out　more　coupled　heat　transfer　analysis　of　turbine　blade　cooling　to　find　the　appropriate　geometric　parameter/configuration　of　internal　and　film　cooling　for　the　fine　design　of　gas　turbine　blade　cooling,　especially　today　when　large-scale　numerical　calculation　has　become　a　reality.　©　2022　Elsevier　Ltd