Blade platform cooling in a gas turbine

A blade for a rotor of a gas turbine, comprising:

• a root for connecting the blade to a disc of the rotor,
• a platform having a lower surface from which the root extends and an upper surface opposite to the lower surface,
• a hollow aerofoil extending from the upper surface of the platform,
• the aerofoil comprising a leading edge and a trailing edge and the platform comprising a leading border upstream the leading edge and a trailing border downstream the trailing edge, the lower surface of the platform comprising an upstream seat and a downstream seat,
• an inner cooling passage inside the hollow aerofoil for channelling a first cooling medium to a first plurality of outlet cooling holes provided on at least an external surface of the hollow aerofoil,
• at least a channel, separated from the inner cooling passage, extending through the platform for channelling a second cooling medium from at least one opening of the channel to a second plurality of outlet cooling holes provided on the upper surface of the platform,
• wherein the at least one opening of the channel is provided on the lower surface of the platform between the leading border and the upstream seat and/or between the downstream seat and the trailing border.