| 摘要 |
1519449 Gas turbine engines - cooling turbine rotor blades ROLLS-ROYCE Ltd 10 Nov 1975 [11 Nov 1974] 48661/74 Heading F1G and FIT The invention relates to a gas turbine engine in which cooling air is directed on'to the tips of the turbine rotor blades whereby the blade tips are cooled and the air is so directed as to augment the torque exerted on the blades by the combustion gas. The gas turbine engine shown comprises a turbine motor (17) having blades 18 to which combustion gases from combustion chamber (12) are directed by inlet nozzle guide vanes 15. Air taken from the compressor (10) is led to a chamber 23 from which it is directed by guide vanes 35 disposed between inner and outer walls 34, 33 on to the tips of the rotor blades 18 as indicated by arrow C Fig. 2 and arrow A Fig. 4. the direction of arrow A is parallel to arrow B which is the direction in which the combustion gases are directed by inlet guide vanes 15 so that the cooling air-flow acts to impart thrust to the rotor blades. The cooling air may first be passed from chamber 24 through axial tubes 27 having orifices 29 by which jets of cooling air are directed on to the outer surface of the rotor blade shroud 22, the cooling air discharging from chamber 25 through the guide vane assembly 35. |
