| CPC F02C 7/057 (2013.01) [F01D 17/08 (2013.01); F01D 17/141 (2013.01); F02C 7/042 (2013.01); F05D 2270/3015 (2013.01)] | 19 Claims |
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11. 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 for providing fluid communication with an environment 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;
a flow restrictor located within the annular inlet duct, the flow restrictor extending across the annular inlet duct and being movable within the annular inlet duct along a circumferential direction relative to the central axis;
an actuator engaged to the flow restrictor, the actuator operable to move the flow restriction along the circumferential direction; and
a controller operatively connected to at least two sensors and the actuator, the controller having a processing unit and a non-transitory computer-readable medium operatively connected to the processing unit and containing instructions executable by the processing unit for:
receiving a signal from the at least two sensors, the signal indicative of a pressure difference between a first pressure within the first section and a second pressure within the second section; and
powering the actuator to move the flow restrictor with the actuator from a first position to a second position circumferentially offset from the first position as a function of the pressure difference.
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