AIRCRAFT ENGINE INTAKE DUCT WITH PASSIVELY MOVABLE FLOW RESTRICTOR

An aircraft engine (10), has: an inlet (12) leading to a compressor section (13), the inlet (12) extending circumferentially around a central axis (A); an annular inlet duct (22) extending circumferentially around the central axis (A), the annular inlet duct (22) having a duct inlet (22A) fluidly connected to an environment outside of the aircraft engine (10) and a duct outlet (22D) fluidly connected to the inlet (22A), the duct outlet (22D) extending circumferentially around the central axis (A); and a flow restrictor (26) located within the annular inlet duct (22), the flow restrictor (26) extending across the annular inlet duct (22), being movable within the annular inlet duct (22) along a circumferential direction (D1) relative to the central axis (A) in response to a fluid pressure differential on opposed sides of the flow restrictor (26).