Patent ID: 8267641

Claim:
A gas turbine, comprising: a rotor shaft; a plurality of rotor blades that extend generally radially outwardly from the rotor shaft, each rotor blade comprises: an aerofoil: a shroud, radially outward of the aerofoil; and a plurality of guide vanes located adjacent to the plurality of rotor blades, the plurality of guide vanes extending generally radially outwardly, wherein the plurality of guide vanes direct gas flowing through the gas turbine onto the plurality of rotor blades, wherein a guide vane accommodates a first flow of a cooling fluid to an aperture in the guide vane that is located in a first region of the guide vane that is adjacent to both a radially outer end of the guide vane and to a trailing edge of the guide vane, wherein the first flow of cooling fluid within the guide vane is substantially directed to the aperture to minimize heat transfer from the guide vane to the cooling fluid, wherein the first flow of cooling fluid emanating from the aperture travels to impinge upon the shroud of the rotor blade thereby the shroud, and wherein the aperture is located in a high pressure side or a low pressure side of the guide vane, wherein the guide vane accommodates a second flow of cooling fluid that maximizes heat transfer from the guide vane to the second flow of cooling fluid, and wherein the second flow of cooling fluid begins at an radially inner end and the radially outer end of the guide vane and ends at the trailing edge of the guide vane.