Detailed　characteristics　of　film　cooling　from　discrete　injection　and　purge　flow,　and　associated　coolant　injection　patterns　are　presented　over　a　turbine　endwall　for　wide　engine-representative　coolant　flow　rate　ranges.　Measurements,　in　combination　with　numerical　simulations,　are　performed　in　a　linear　cascade　that　is　geometrically　and　aerodynamically　scaled　up　from　the　hub　section　of　the　turbine　vane.　Reynolds　numbers　at　the　vane　cascade　inlet　are　varied　from　1.40　×　105　to　4.20　×　105,　representing　the　variations　of　real　engine　operating　conditions　(from　take-off　to　cruise　conditions).　In　order　to　examine　the　isolated　and　combined　cooling　effects,　discrete　coolant　injection　and　purge　flow　for　the　endwall　cooling　can　be　injected　separately　or　simultaneously.　Numerical　simulations　are　conducted　to　gain　further　insight　into　interactions　between　endwall-nearby　secondary　flows　and　coolant　injection.　Additionally,　a　net　heat　flux　reduction　parameter　is　used　to　evaluate　overall　film　cooling　performance　of　the　cooling　scheme,　that　takes　heat　transfer　enhancement　by　coolant　injection　into　consideration.　Results　show　that　endwall-nearby　flow　structures　dictate　thermal　protection　patterns.　Increasing　coolant　flow　rates　decreases　effectiveness　values　of　discrete　film　cooling　but　improves　cooling　effectiveness　of　purge　flow.　In　spite　of　no　direct　interactions　between　discrete　injection　and　purge　flow,　adding　purge　flow　could　help　enhance　discrete　film　cooling　effectiveness.　Higher　passage　inlet　Reynolds　number　leads　to　reduced　mixing　of　coolant　injection　and　mainstream　flows,　resulting　in　improved　effectiveness　values.　Changing　trends　of　overall　cooling　performance　for　purge　flow　and　discrete　film　cooling　by　increasing　coolant　flow　rates　are　opposite　but　those　are　the　same　by　increasing　Reynold　numbers.　©　2020　Elsevier　Ltd