| 摘要 |
A blade (20) for a rotor (15) of a gas turbine (10) comprises: - a root (22), - a platform (24) having a lower surface (31) and an upper surface (30) opposite to the lower surface (31), - a hollow aerofoil (26), - an inner cooling passage (46) inside the hollow aerofoil (26) for channelling a first cooling medium to a first plurality of outlet cooling holes (40) on an external surface (28) of the hollow aerofoil (26), - a channel (62), separated from the first cooling circuit (50), extending through the platform (24) for channelling a second cooling medium from at least one opening (65, 66) of the channel (62) to a second plurality of outlet cooling holes (72) provided on the upper surface (30) of the platform (24), wherein the at least one opening (65, 66) of the channel (62) is provided on the lower surface (31) of the platform (24) in order to receive in operation the second cooling medium from an inner cavity (16) of the rotor (15). |
