Modern　gas　turbine　blade　is　operating　at　high　temperature　which　requires　abundant　cooling.　Considering　both　heat　transfer　rate　and　pumping　power　for　internal　passages,　developing　efficient　cooling　passages　is　of　great　importance.　Ribbed　channel　has　been　proved　as　effective　heat　transfer　enhancement　technology　for　considerable　heat　transfer　characteristics;　however,　the　pressure　loss　is　impressive.　Dimple　and　protrusion　are　frequently　considered　as　new　heat　transfer　augmentation　tools　for　their　low　friction　loss　in　recent　years.　Numerical　simulations　are　adopted　to　investigate　the　thermal　performance　of　rectangular　channel　with　compound　heat　transfer　enhancement　structures　with　ribs,　dimples,　and　protrusions.　Among　all　configurations,　the　nondimensional　dimple/protrusion　depths　are　0.2.　The　results　present　the　flowstructures　of　all　channel　configurations.　The　Nu/Nu(0)　distributions　of　channel　section　are　discussed　for　each　case.　The　pressure　penalty　f/f(0)　and　the　thermal　performance　TP　are　also　considered　as　important　parameters　for　heat　transfer　enhancement.　It　can　be　concluded　that　the　optimal　structure　of　the　compound　heat　transfer　enhancement　structure　is　rib　+　protrusion　(D=6mm)　+　dimple　(D=15mm).