| 摘要 |
A turbine aerofoil (20) for a gas turbine has a pressure wall (26) and suction wall (28) and at least one internal cavity (24). An aerofoil platform (16,18) adjacent and generally perpendicular to the aerofoil has at least one internal cavity (41) with a pressure wall (42) and suction wall (44) on respective sides of the cavity. The cavity (41) is divided into at least two cooling chambers (48,50) including a first chamber (48) for receiving cooling air for the platform pressure wall and a second chamber (50) for receiving cooling air for cooling the platform suction wall. The first chamber is in flow communication with the aerofoil cavity for discharge of at least part of the cooling air entering the first chamber to the aerofoil cavity. |
