| 摘要 |
837,575. Gas-turbine bladed rotors. GENERAL ELECTRIC CO. Nov. 29, 1957 [Dec. 26, 1956], No. 37270/57. Class 110 (3). A gas-turbine rotor comprises a rotor disc 2 with blades mounted on the periphery thereof, each blade comprising a root portion 12, a stem 10 and a working portion 6, passages 68 for flow of cooling fluid being provided between adjacent blade stems. The cooling fluid passages 68 are sealed from the working fluid passage by means of an annular member 54 which is formed with axially-extending fingers 60 which are disposed beneath the blade platforms 8, the blade stems 10 being received in notches 58 formed in the annular member between the fingers 60. The annular member is of angle section and is held in position axially by means of a plate member 26 which lies adjacent one face of the rotor disc and defines therewith a cooling fluid supply passage 46 leading to the passages 68 between the blade stems. The plate 26 has a central hub 30 which is mounted on the shaft 4 and may either be freely mounted or secured thereto. Cooling fluid such as air under pressure is supplied from the space 49 through openings 48 in the plate 26 thence through the space 46 between the plate and the rotor disc to the passages 68 between the blade stems. Alternatively the shaft 4 may be hollow and connected to the rotor disc 2, openings being provided in the shaft between the plate 26 and disc 2 so that cooling air fed through the hollow shaft may flow into the space 46 between the plate and the disc. Radial vanes 50 may be disposed on the inner surface of the disc 26. The stem portion 10 of each blade diverges towards the underside of the blade platform and the edges of the fingers 60 bear against the divergent surfaces under centrifugal action. |
