| 摘要 |
695,221. Compressor rotors. ARMSTRONG SIDDELEY MOTORS, Ltd. Oct. 18, 1951 [Dec. 8, 1950], No. 30065/50. Class 110(iii) An axial flow compressor rotor, particularly for a gas turbine engine, comprises a series of discs most of which have axially-disposed extensions 22 at their peripheries, the extensions forming shrouds between adjacent rows of rotor blades 33 and the axial extremities of the extensions being spigotally engaged at 23, 24 with the next disc. Each two adjoining discs together provide a peripheral groove 31 in which the blade roots are accommodated. The discs are secured together by bolts 25 disposed inwardly of the blade roots and the axes of the bolts lie on a pitch circle which is coincident with the cylindrical surface of the spigotal connection. The discs 21 are of aluminium or other light alloy and have slightly enlarged hollow hubs 50 for the passage of cooling air. The bolts 25 have shoulders 26 which bear against radial faces of the extensions 22 and are secured thereto by nuts 29. The adjacent discs are secured by nuts 30. The end discs 19, 20 are of steel and have shaft portions 17, 18 journaled in bearings mounted in the casing diaphragms 13, 14. The end disc 20 at the outlet end of the compressor is spigotally engaged with the adjacent disc 21 in the manner described above, but the end disc 19 is connected to a separate ring 22a of light alloy by means of a spigot connection and bolts 25a, a row of rotor blades being clamped therebetween. The blades may be of plastic moulded to shape and incorporating a filler of asbestos or other heat-resisting material. The blade roots may be of T, dovetail or fir-tree section and may be of parallelogram shape in plan view with both the axially- and circumferentially-directed faces tapering outwardly, spacers being disposed between the circumferential faces of the blade roots when assembled. |
