Patent ID: 11933220
Assignee: PRATT & WHITNEY CANADA CORP.
Field: nan (nan)
Classification: CPC nan | IPC F

Claim 6:
7. A propulsion system for an aircraft, the propulsion system comprising:
a gas turbine engine forming a core flow path;
an air intake, the air intake including an air inlet duct, a core flow duct, a bypass flow duct, a splitter, and a flow control device, the air inlet duct including an intake inlet of the air intake, the core flow duct including a core flow outlet, the core flow duct extending between and to the air inlet duct and the core flow outlet; the core flow duct configured to direct air from the air inlet duct to the core flow path through the core flow outlet, the bypass flow duct includes a bypass flow outlet, the bypass flow duct extending between and to the air inlet duct and the bypass flow outlet, the bypass flow duct forming a bypass flow passage from the air inlet duct to the bypass flow outlet, the splitter separating the core flow duct and the bypass flow duct, the air inlet duct and the bypass duct forming a gas path floor of the air intake, the gas path floor facing the splitter, the flow control device includes an inflatable boot and a fluid regulator, the inflatable boot is disposed the gas path floor, the fluid regulator in fluid communication with the inflatable boot, the fluid regulator configured to selectively position the inflatable boot in a fully inflated position, a fully deflated position, and a plurality of intermediate inflation positions between the fully inflated position and the fully deflated position; and
an engine control system, the engine control system in signal communication with the fluid regulatory, the engine control system including a processor in communication with a non-transitory memory storing instructions, which instructions when executed by the processor, cause the processor to:
identify that an icing condition is present or absent for the propulsion system; and
control the fluid regulator to selectively position the inflatable boot in the fully deflated position to control an air flow path for air flowing through the air inlet duct, the core flow duct, and the bypass flow duct based on identification that the icing condition is present for the propulsion system.