AIRCRAFT INTAKE DUCT WITH ACTIVELY MOVABLE FLOW RESTRICTOR

An aircraft engine (10), has: an inlet (12) extending circumferentially around a central axis (A); an annular inlet duct (22) having a duct inlet (22A) fluidly connected to an environment outside of the aircraft engine (10) and a duct outlet (220) fluidly connected to the inlet (22A); a flow restrictor (26) extending across the annular inlet duct (22) and being movable within the annular inlet duct (22); an actuator (31) engaged to the flow restrictor (26) and operable to move the flow restrictor (26); and a controller (34) operatively connected to at least one sensor (32A, 328, 33A, 33B) and the actuator (31), the controller (34) having a processing unit (702) and a computer-readable medium (704) operatively connected to the processing unit (702) and containing instructions (706) for: receiving a signal indicative of a pressure difference between opposite sides of the flow restrictor (26); and powering the actuator (31) to move the flow restrictor (26) with the actuator (31) from a first position to a second position offset form the first position as a function of the pressure difference.