Patent ID: 9624777
Date: 2017-04-18
CPC Classifications: F01D,F05D

Claim:
1. A rotor of an aircraft turbomachine having a main axis A, which comprises means for modifying a critical speed of the rotor between a first critical speed and a second critical speed, depending on whether the rotational speed of the rotor is lower or higher than a predefined rotational speed between the first critical speed and the second critical speed, said means for modifying the critical speed of the rotor comprising: a component that is capable of occupying a first state or a second state depending on whether the rotational speed of the rotor is lower or higher than the predefined rotational speed, each state of the component corresponding to a critical speed of the rotor, and means for driving the component towards one or the other of the two states thereof, depending on the rotational speed of the rotor, wherein the means for modifying the critical speed of the rotor further comprise a component that engages with the drive means and is capable of being deformed elastically between one or the other of two stable forms, each of which corresponding to a state of said component.