Patent ID: 8128366

Claim:
An apparatus for use in a gas turbine engine, the apparatus comprising: a wall defining an exterior face; a first film cooling passage extending through the wall to a first outlet along the exterior surface of the wall for providing film cooling, wherein the first film cooling passage defines a first interior surface region and a second interior surface region; a first row of vortex-generating structures located along the first interior surface region of the first film cooling passage, wherein the first row of vortex-generating structures comprises a first row of chevron-shaped ribs each having an apex; and a second row of vortex-generating structures located along the second interior surface region of the first film cooling passage, wherein the second row of vortex-generating structures comprises a second row of chevron-shaped ribs each having an apex, and wherein the apexes of the chevron-shaped vortex-generating ribs of the first and second rows face in opposite directions, and wherein the first and second rows of vortex-generating structures are configured to induce a pair of vortices in substantially opposite first and second rotational directions in a cooling fluid passing through the first cooling passage prior to reaching the first outlet.