| 摘要 |
844,896. Turbine and compressor-bladed rotors. UNITED AIRCRAFT CORPORATION. Jan. 29, 1958 [Feb. 11, 1957], No. 2952/58. Class 110 (3). In a turbine or compressor-blade rotor in which a plurality of blades is mounted around the periphery of the rotor disc with provision for limited movement of the blades with respect to the disc, inter-engaging projections and recesses are provided on the blade platforms to provide frictional damping of the limited movement. The blade 14 has a platform 20 and a root portion 36 which is received in the circumferential recess 40 formed between flanges 44, 46 at the periphery of the rotor disc 10. The blade is pivotally mounted on a bolt member 48 which passes through a bore 38 in the blade root and is in screwed engagement with the flange 46. The head of the bolt is received in an opening 54 in the flange 44 and bears against the blade root so that the blade root will tend to move to the right as seen in Fig. 4 as the bolt 48 is tightened. In the case of the adjacent blade 12 a washer 60 is disposed between the blade root 62 and the flange 46 so that the axial position of the blade 12 is fixed. The platform 20 of the blade 14 is formed with notches 22 and projections 28 which inter-engage with corresponding projections and notches 26, 24 on the platforms 18 of the adjacent blades. The interengaging faces of the projections 26, 28 are shown at 30, 32 and the pressure at the interengaging faces may be determined by the axial position of the bolt 48, this pressure acting to damp movement of. the blades about their pivot mountings. In a second embodiment, a spring washer is disposed between the head of the pivot bolt and the side of the blade root of alternate blades so that wear is taken up automatically. Alternatively some of the projections on the blade platforms may be inclined to planes normal to the rotor axis so that if there is relative motion between adjacent platforms about their respective pivot mountings, the friction between adjacent surfaces will vary. |
