Patent ID: 11919654
Assignee: PRATT & WHITNEY CANADA CORP.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC B  F | IPC B  F

Claim 8:
9. An intake for an aircraft engine, comprising:
an annular inlet duct extending circumferentially around a central axis, the annular inlet duct having a duct inlet fluidly connected to an environment outside of the aircraft engine and a duct outlet extending circumferentially around the central axis, the annular inlet duct defining:
a first section extending from the duct inlet towards a location being diametrically opposed to the duct inlet, and
a second section extending from the duct inlet towards the location, the second section opposite the first section; and

a flow restrictor located within the annular inlet duct, the flow restrictor extending across the annular inlet duct and fluidly separating the first section from the second section, the flow restrictor movable within the annular inlet duct along a circumferential direction relative to the central axis as a result of a pressure difference between a first pressure within the first section and a second pressure within the second section.