Rotor support device, rotor, gas turbine engine, and aircraft

A rotor support device comprising:

• a plurality of first electrodes;
• a plurality of second electrodes;
• one or more dielectric materials disposed between the plurality of first electrodes and the plurality of second electrodes;
• one or more AC power supplies configured to apply an alternating-current voltage across the plurality of first electrodes and the plurality of second electrodes and induce flows of gas by causing dielectric barrier discharge between the plurality of first electrodes and the plurality of second electrodes;
• and
• one or more circuits, wherein
• at least a pair of electrodes are disposed apart from each other in a static system that is stationary with respect to a rotor provided in an aircraft, the static system being adjacent to the rotor, the pair of electrodes including at least one of the plurality of first electrodes or the plurality of second electrodes,
• the one or more circuits stores at least one of a table and a function in which predetermined electrodes out of the at least one of the plurality of first electrodes or the plurality of second electrodes are associated with a number of revolutions of the rotor, and
• the one or more circuits are configured to apply the alternating-current voltage to the predetermined electrodes based on the at least one of the table and the function and the number revolutions of the rotor.