Apparatus and method for controlling a compressor
AssigneesPratt & Whitney Canada Corp., Polyvalor S.E.C.
InventorHuu Duc VO
Life of this patent
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Abstract
A compressor comprises a casing having an inner surface surrounding a rotor assembly, the rotor assembly having a plurality of circumferentially spaced radially outwardly extending rotor blades, each blade having leading and trailing edges and a tip, the compressor further comprising at least one plasma actuator for suppressing rotating stall inception of the compressor, the at least one plasma actuator being mounted adjacent to the blade tips.
Claims22
A compressor comprising:
- a casing having an inner surface surrounding a rotor assembly, the rotor assembly having a plurality of circumferentially spaced radially outwardly extending rotor blades, each blade having leading and trailing edges and a tip, the compressor further comprising at least one plasma actuator for suppressing rotating stall inception of the compressor, the at least one plasma actuator being mounted adjacent to the blade tips.
A method for suppressing rotating stall inception of a compressor, the compressor including a casing having an inner surface surrounding a rotor assembly, the rotor assembly having a plurality of circumferentially spaced radially outwardly extending rotor blades, each blade having leading and trailing edges and a tip, the method comprising actuating at least one plasma actuator disposed circumferentially around the casing near the blade tips of the rotor assembly to induce axial flow acceleration within a tip clearance gap region of the rotor assembly.
A method for suppressing rotating stall inception of a compressor, the compressor including a casing having an inner surface surrounding a rotor assembly, the rotor assembly having a plurality of circumferentially spaced radially outwardly extending rotor blades, each blade having leading and trailing edges and a tip, the method comprising actuating independent adjacent plasma actuator sections around the casing near the blade tips of the rotor assembly to induce circumferentially varying axial flow acceleration within a tip clearance gap region of the rotor assembly, thereby resulting in a circumferential perturbation in pressure rise around the compressor.
Dependencies are inferred from the claim text.