To　cool　a　high-pressure　gas　turbine　blade,　many　rows　of　cooling　holes　with　different　arrangements　and　configurations　are　manufactured　to　achieve　higher　cooling　effect　and　lower　aerodynamic　loss.　To　evaluate　the　heat　transfer　and　film　cooling　effect　in　the　full-cooled　turbine　blade,　efficient　numerical　simulations　are　required　in　the　design　and　performance　optimization　processes.　From　the　view　of　numerical　accuracy,　the　structured　grids　have　to　be　employed　because　of　higher　resolution　in　flow　and　heat　transfer　than　the　unstructured　grids.　Because　many　splitting,　attaching　and　merging　manipulations　are　involved　in　meshing　the　cooling　features　and　curved　boundaries,　it　is　very　complex　and　time-consuming　for　a　researcher　to　generate　multi-block　structured　grids　for　a　full-cooled　gas　turbine　blade.　As　a　result,　in　the　industrial　applications,　almost　all　researchers　preferred　to　generate　unstructured　grids　instead　of　structured　grids　for　the　full-cooled　blade.　Unlike　the　previous　research,　the　aim　of　this　study　is　to　apply　the　Background-Grid　Based　Mapping　(BGBM)　method　proposed　in　Part　I　to　generate　multi-block　structured　grids　for　a　full-cooled　gas　turbine　vane.　With　the　strategy　of　BGBM　method,　meshes　were　conveniently　generated　in　the　computational　space　with　simple　geometrical　features　and　plain　interfaces,　and　then　were　mapped　back　into　physical　space　to　obtain　the　multi-block　structured　grids　which　can　be　used　for　numerical　simulations.　With　the　experimental　data,　the　present　numerical　methods　and　BGBM　strategy　were　carefully　validated.　Then,　the　flow　and　film　cooling　performance　in　the　full-cooled　NASA　GE-E3　nozzle　guided　vane　were　numerically　investigated.　The　effects　of　coolant　mass　flow　rate　and　land　extensions　on　film　cooling　effectiveness　were　discussed.　The　results　show　that　film　cooling　effectiveness　near　the　stagnation　point　is　the　lowest　and　film　cooling　effectiveness　on　the　pressure　side　is　slightly　higher　than　that　on　the　suction　side.　When　the　coolant　mass　flow　rate　increases　up　to　the　value　of　1.5　design　flow,　the　relative　outflow　mass　flow　rates　of　cooling　hole　arrays　and　slots　are　no　longer　affected　by　the　increase　of　the　coolant　flow　rate.　At　half　design　flow,　the　outflow　mass　flow　rates　of　No.5　hole-array　to　No.10　hole-array　are　almost　zero,　and　the　area-averaged　film　cooling　effectiveness　on　vane　surface　is　as　low　as　0.268.　Compared　with　the　cases　of　half　design　flow　and　double　design　flow,　better　film　cooling　performance　is　obtained　in　the　cases　of　design　flow　and　1.5　design　flow.　Compared　with　the　vane　without　lands,　the　area-average　cooling　effectiveness　on　vane　surface　is　slightly　higher　for　the　vane　with　lands.　Land　extensions　have　a　considerable　influence　on　film　cooling　performance　in　the　cutback　region.　Copyright　©　2020　ASME