US Patent 7648333 Cooling arrangement

A cooling arrangement 21 for use within a gas turbine engine comprises a first shroud or platform 26 incorporating coolant passages 25 and a second shroud or platform 28. Generally, each platform or shroud 26, 28 will incorporate a pressure portion and a suction portion, with the pressure portion incorporating the coolant passages 25 through which the coolant flow 27 becomes incident on a surface 40 of the suction portion of the second shroud 28. The surface 40 is inclined or tapered towards the passage 25, such that there is limited direct impingement upon a front edge 39 of the surface 40. The coolant flow 27 thereby remains adjacent to the surface 40 for a longer period and so enhances cooling efficiency.