An aircraft engine, has: an inlet leading to a compressor section, the inlet extending circumferentially around a central axis; an annular inlet duct extending circumferentially around the central axis, the annular inlet duct having a duct inlet fluidly connected to an environment outside of the aircraft engine and a duct outlet fluidly connected to the inlet, the duct outlet extending circumferentially around the central axis; and a flow restrictor located within the annular inlet duct, the flow restrictor extending across the annular inlet duct, being movable within the annular inlet duct along a circumferential direction relative to the central axis in response to a fluid pressure differential on opposed sides of the flow restrictor.
AIRCRAFT INTAKE DUCT WITH PASSIVELY MOVABLE FLOW RESTRICTOR
CONDUITE D'ENTREE D~AIR D~AERONEF COMPRENANT UN LIMITEUR DE DEBIT PASSIVEMENT MOBILE
2024-02-05
Patent
Electronic Resource
English
AIRCRAFT INTAKE DUCT WITH PASSIVELY MOVABLE FLOW RESTRICTOR
European Patent Office | 2024
|Aircraft intake duct with passively movable flow restrictor
European Patent Office | 2024
|