| 摘要 |
995,514. Turbine and compressor blades. UNITED AIRCRAFT CORPORATION. July 5, 1963 [July 6, 1962], No. 26666/63. Heading FIT. A compressor or turbine blade vibration damping device mounted on the periphery of a rotor disc comprises a cover plate attached to one side of the disc and having circumferentially spaced lugs, and a damper element for each blade mounted between the cover plate and the associated blade having respective surfaces which frictionally engage one of the lugs and an abutment surface on the associated blade when the rotor is rotating. A compressor or turbine blade 8, Fig. 3, comprises a dovetail root 6 mounted in an axial slot in the rotor disc, a root extension 10, and a platform 14 adjoining the working portion 12. Annular cover plates 18, 20, Fig. 2, riveted at 22 retain each blade 8 axially in its slot. Circumferentially spaced lugs 30 extend axially inwardly from radial fingers 31 on cover plate 20 and co-operate with vibration damping elements 24. Each element 24 has a base 26, Fig. 5, with a circumferential surface 28 in frictional contact with the radially inner face of lug.30, an oblique arm 32, and an outer surface 34 frictionally engaging the underside of the associated blade platform 14 under centrifugal action.
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