Patent ID: 11384687

Abstract:
An anti-icing system for a gas turbine engine comprises a closed circuit containing a phase-change fluid, at least one heating component for boiling the phase-change fluid, the anti-icing system configured so that the phase-change fluid partially vaporizes to a vapour state when boiled by the at least one heating component. The closed circuit has an anti-icing cavity adapted to be in heat exchange with an anti-icing surface of the gas turbine engine for the phase-change fluid to release heat to the anti-icing surface and condense. A feed conduit(s) has an outlet end in fluid communication with the anti-icing cavity to feed the phase-change fluid in vapour state from heating by the at least one heating component to the anti-icing cavity, and at least one return conduit having an outlet end in fluid communication with the anti-icing cavity to direct condensed phase-change fluid from the anti-icing cavity to the at least one heating component. A method for heating an anti-icing surface of an aircraft is also provided.