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

1. 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.

2. The rotor support device according to claim 1 , wherein the at least one of the plurality of first electrodes or the plurality of second electrodes is disposed apart from each other on an annular casing surrounding the rotor disposed in at least one of an intake fan, a compressor, or a turbine of a gas turbine engine provided in the aircraft.

3. The rotor support device according to claim 1 , wherein the at least one of the plurality of first electrodes or the plurality of second electrodes is disposed apart from each other in a stator adjacent to the rotor provided in at least one of a compressor or a turbine of a gas turbine engine provided in the aircraft.

4. The rotor support device according to claim 1 , wherein the at least one of the plurality of first electrodes or the plurality of second electrodes is disposed apart from each other on an annular casing surrounding a tail rotor provided in a rotary-wing aircraft.

5. The rotor support device according to claim 1 , wherein the at least one of the plurality of first electrodes or the plurality of second electrodes is disposed apart from each other on an annular casing surrounding a fan provided as the rotor in each of main wings or a fuselage of a fixed wing aircraft.

6. The rotor support device according to claim 1 , wherein both the plurality of first electrodes and the plurality of second electrodes are disposed apart from each other in the static system.

7. The rotor support device according to claim 1 , wherein

one of the plurality of first electrodes and the plurality of second electrodes is disposed apart from each other in the static system, and

the other of the plurality of first electrodes and the plurality of second electrodes is attached to a plurality of blades provided in the rotor.

8. The rotor support device according to claim 1 , wherein the number of the at least one of the plurality of first electrodes or the plurality of second electrodes disposed apart from each other in the static system is equal to a number associated with the number of revolutions of the rotor.

9. The rotor support device according to claim 1 , wherein lengths, in a rotational direction of the rotor, of the at least one of the plurality of first electrodes or the plurality of second electrodes disposed apart from each other in the static system are lengths associated with the number of revolutions of the rotor.

10. The rotor support device according to claim 2 , wherein the number of the at least one of the plurality of first electrodes or the plurality of second electrodes disposed apart from each other on the annular casing is equal to the number of intermittent flows of gas for preventing leak flows of gas generated between tips of blades provided in the rotor and the annular casing, the intermittent flows of gas being induced between the tips of the blades provided in the rotor and the annular casing via the dielectric barrier discharge by rotating the blades provided in the rotor about a rotary shaft of the rotor.

11. The rotor support device according to claim 3 ,

wherein the number of the at least one of the plurality of first electrodes or the plurality of second electrodes disposed apart from each other in the stator is equal to the number of intermittent flows of gas for improving energy efficiency when the aircraft flies at stable speed or intermittent flows of gas for stabilizing unstable speed when the aircraft flies at the unstable speed, the intermittent flows of gas being induced between rotor blades and the stator via the dielectric barrier discharge by rotating the rotor blades provided in the rotor about a rotary shaft of the rotor.

12. A rotor comprising:

the support device according to claim 1 .

13. A gas turbine engine comprising:

the support device according to claim 2 ; and

the rotor.

14. An aircraft comprising:

the gas turbine engine according to claim 13 .

15. An aircraft comprising:

the rotor according to claim 12 .

16. The rotator support device according to claim 1 , wherein the rotor includes a blade, and the one or more circuits are configured to apply the alternating-current voltage to the predetermined electrodes to induce flows of gas between the predetermined electrodes and a tip of the blade so that the flows of gas are substantially same as flows of gas between the predetermined electrodes and the tip of the blade in a state where an alternating-current voltage having a burst waveform is applied to the predetermined electrodes.