| 摘要 |
933,047. Turbine and compressor bladed rotors. GENERAL ELECTRIC CO. Feb. 20, 1962 [Feb. 23, 1961], No. 6469/62. Class 110(3). A rotor assembly for a gas-turbine engine, for example an axial-flow compressor rotor, comprises a series of rotor discs 11 having axially-extending slots formed in their rim portions 12 in which the root portions of the rotor blades are mounted. The blades are formed with platform portions 20, and a spacer ring 24 is provided to fit between the platform portions of adjacent blade rows, the ring having a portion 26 which co-operates with the blade platforms 20 to form the inner wall of the fluid flow path. The spacer ring is also formed with a pair of offset rim portions 30, 33 which bear against the undersides of the rim portions 12 of the adjacent rotor discs. The spacer ring is split at one point in its periphery, the adjacent ends of the ring being adapted to be relatively displaceable whereby one end portion may be displaced sufficiently radially inwardly to permit removal of a rotor blade. The split in the spacer ring 24 is shown at 35 in Fig. 3, the split being of zig-zag form, as shown, so that the two parts tend to lock together in their normal position. The two ends may be additionally secured together by means of a bolt member 40. The end 37 of the spacer ring is shown displaced radially inwardly in Fig. 5, to permit removal of a blade 16. The blade roots 18 are provided with lugs 22, as shown in Fig. 5, to limit axial movement in one direction, and a plate 44 may be secured to the ring 24 to engage between a pair of the blade lugs 22 so as to prevent circumferential movement of the spacer ring during operation. In a second embodiment, one end of the spacer ring is formed with an axially-extending recess in its outer periphery and the other end with an axiallyextending lug on its inner periphery the recess normally engaging with the lug but being displaceable radially inwardly therefrom. |
