| 摘要 |
A gas turbine engine fan blade ( 22 ) and disk assembly ( 30 ) is provided with levers ( 36 ) with which to apply a force to the radially inner end of respective blades ( 22 ) so as to move the roots ( 26 ) of the blades ( 22 ) into abutting engagement with the side walls of the inverted "V" shaped grooves ( 32 ) in the disk rim ( 34 ), and thereby prevent relative wearing movement therebetween. The levers ( 36 ) are appropriately moved by rotation of respective screws ( 52 ) that pass through exposed ends thereof in screw threaded engagement, and abut a fixed land ( 46 ) so as to apply a pivoting force on each lever ( 36 ).
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