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
05.03.2024
Patent
Elektronische Ressource
Englisch
AIRCRAFT INTAKE DUCT WITH PASSIVELY MOVABLE FLOW RESTRICTOR
Europäisches Patentamt | 2024
|AIRCRAFT INTAKE DUCT WITH PASSIVELY MOVABLE FLOW RESTRICTOR
Europäisches Patentamt | 2024
|