GB319622A - Gas turbine - Google Patents

Abstract

319,622. Kalßbek, V. Sept. 24, 1928, [Convention date]. Cooling parts; blades. - A gas turbine is cooled by passing through the wheels and blades a gaseous cooling medium, such as air or steam, at a pressure approximately equal to the pressure in the stage of the turbine to which it is admitted. The cooling medium passes through the blades into the working fluid stream, and gives up energy. Fig. 1 shows the application to a gas turbine, the first stage 1 of which has a double ring of rotor blades, the second and third stages 2, 3 having single rings. Cooling g medium is introduced by a pipe 12 and a channel K in the rotor boss to outwardly extending passages in the first rotor 1, from which it passes by channels in the blades into the surrounding chamber A and also into the blade spaces which are at the moment being fed by the first nozzle D. The cooling medium in the chamber A passes through slots s into the second nozzle E. The second rotor 2 and the third nozzle F are cooled in a similar manner by gas led in by a pipe 14. The last rotor 3 is cooled by an atmospheric air drawn through a grid v and forced outwards by centrifugal action in the rotor. The fixed blades 11 in the first stage are cooled by compressed air &c. introduced at 13. The casing members 9, 10 may be water-jacketed. The rotor blades are fixed by being clamped between adjacent sections of the rotor, and spacing pieces are: arranged in the channels in the rotor. The blades, Fig. 6, are formed of two parts 33, 36 connected together so as to leave a passage 35 between them. The cooling medium, which enters through a restricted opening 40, may escape into the stream of working-fluid at the periphery 37, or at one or both sides of the blade. One edge 39, Fig. 12, of the blade may be turned over so as to deflect the issuing air along the face of the blade. A shrouding ring is fixed to the tips 38.