| 摘要 |
A gas turbine including a rotor shaft, a plurality of rotor blades that extend generally radially outwardly from the rotor shaft, each rotor blade including a shroud radially outward of an aerofoil, and a plurality of guide vanes located adjacent to the plurality of rotor blades, the plurality of guide vanes also extending generally radially outwardly is provided. The guide vanes operate to direct gas flowing through the turbine onto the rotor blades. A guide vane accommodates a flow of cooling fluid to an aperture in the guide vane that is located in a region that is adjacent both the radially outer end of the guide vane and the trailing edge of the guide vane. The flow of cooling fluid emanating from the aperture travels to impinge upon the shroud thereby cooling the shroud. The aperture is located in the high or low pressure side of the guide vane. |
