Cooled component for a gas turbine engine

A cooled component for a gas turbine engine, the component comprising:

• a segment region defining a segment of an annulus for passage of hot gases therethrough, said segment region having a pair of opposed side faces configured to lie substantially adjacent respective corresponding side faces of the segments of similar operationally and circumferentially adjacent components, wherein:
• the segment region includes an elongate cooling slot in at least one of said side faces, said cooling slot being arranged in fluid communication with at least one flow passage within said segment region for a supply of cooling fluid to said slot,
• the slot is substantially closed at an upstream end of the slot and open at a downstream end of the slot so as to define an outlet for said cooling fluid at an operationally downstream region of said at least one of said side faces, and
• the slot is open along a length of the slot such that, in use, the cooling fluid can travel along the length of the slot and impinge against a segment region of an adjacent component.