Patent attributes
A component, e.g. an aerofoil component like a turbine-blade or guide-vane, for a gas turbine engine, including first and second walls defining at least one passage for supply of cooling fluid to a portion of the component to be cooled, the portion including a slot via which cooling fluid passes from the passage to exit of slot for effecting cooling of the portion, wherein the slot includes at least one side wall, pair of opposite side walls, each having surface profile defining array of channels for passage of cooling fluid, and surface profile defining each of arrays of channels is undulating with the respective arrays of channels in two side walls being angled with respect to one another. The resulting internal cross-corrugated cooling arrangement promotes enhanced cooling of the trailing edge or other portion of the component by controlling flow rate of cooling air through slot and exhausted therefrom.
