A gas turbine engine component, comprising: an airfoil section extending from a platform; a cooling passage located in said platform, said cooling passage including a first wall and a second wall bounding said cooling passage, said first wall having a plurality of first surface features and said second wall having a plurality of second surface features; wherein said plurality of first surface features and said plurality of second surface features are arranged such that a width of said cooling passage varies along a length of said cooling passage, said plurality of first surface features having a first profile, and said plurality of second surface features having a second, different profile, wherein each of the second surface features is a grooved surface distributed along the second wall, the grooved surface being a surface having one or more depressions arranged at spaced intervals, or protrusions extending into the cooling passage formed by a core, each having a projection intersecting a tangent line defined by an adjacent surface, rather than being tangential to the adjacent surface; and wherein the gas turbine component further comprises: a plurality of internal features formed within said cooling passage; and wherein a convergent portion of at least one of said plurality of first surface features is aligned with at least one of said plurality of internal features, wherein a convergent portion of at least one of said plurality of second surface features is aligned with at least one of said plurality of internal features. an airfoil section extending from a platform; a cooling passage located in said platform, said cooling passage including a first wall and a second wall bounding said cooling passage, said first wall having a plurality of first surface features and said second wall having a plurality of second surface features; wherein said plurality of first surface features and said plurality of second surface features are arranged such that a width of said cooling passage varies along a length of said cooling passage, said plurality of first surface features having a first profile, and said plurality of second surface features having a second, different profile, wherein each of the second surface features is a grooved surface distributed along the second wall, the grooved surface being a surface having one or more depressions arranged at spaced intervals, or protrusions extending into the cooling passage formed by a core, each having a projection intersecting a tangent line defined by an adjacent surface, rather than being tangential to the adjacent surface; and wherein the gas turbine component further comprises: a plurality of internal features formed within said cooling passage; and wherein a convergent portion of at least one of said plurality of first surface features is aligned with at least one of said plurality of internal features, wherein a convergent portion of at least one of said plurality of second surface features is aligned with at least one of said plurality of internal features. a plurality of internal features formed within said cooling passage; and wherein a convergent portion of at least one of said plurality of first surface features is aligned with at least one of said plurality of internal features, wherein a convergent portion of at least one of said plurality of second surface features is aligned with at least one of said plurality of internal features.