| 摘要 |
1,213,347. Rotor blade fixing. UNITED AIRCRAFT CORP. June 26, 1968 [Aug.16, 1967], No.30354/68. Heading F1T. To reduce vibration of the blades of a compressor of fan rotor in a gas turbine engine each blade is mounted on the rotor by a pin passing through holes in the blade root and in the rotor with clearance to permit rolling of the pin and each blade differs from an adjacent blade in the diameter of the pins and/or holes and/or in the distance of the pin axes from the rotor axis. Thus each blade has a different natural frequency to an adjacent blade. In one embodiment, the blades are mounted on the rotor 74 in similar groups of three, e.g. 50 to 52 or 53 to 55, and the pins 60 to 62 or 63 to 65 in each group are at different distances from the rotor axis. Alternatively, the blades may be mounted on the rotor at only two different radii so that every other blade is on the same radius. The different radii can be combined with, or replaced by, different diameter pins and/or holes. |
