| 摘要 |
<p>The rotor of especially a gas turbine has each rotor blade anchored by its root in an axial slot in the body of the rotor and secured by locking plates (27) which have a kite-like and especially a parallelogram or rhomboid-like base contour and which are fitted in a position between the rotor body and rotor blades and then in an assembly position rotated relative to the inserted position into the annular slots (28,29) formed in the rotor body and in the blades. An independent claim is included for a gas turbine, especially an aviation jet engine, which has at least one rotor as described.</p> |
