An engine bleed control system for a gas turbine engine of an aircraft is provided. The engine bleed control system includes an engine bleed tap coupled to a fan-air source or a compressor source of a lower pressure compressor section before a highest pressure compressor section of the gas turbine engine and a motorized compressor in fluid communication with the engine bleed tap. The engine bleed control system also includes a controller operable to selectively drive the motorized compressor to boost a bleed air pressure from the engine bleed tap as pressure augmented bleed air and control delivery of the pressure augmented bleed air to an aircraft use.
ENGINE BLEED SYSTEM WITH MOTORIZED COMPRESSOR
SYSTEME DE PRELEVEMENT REACTEUR A COMPRESSEUR MOTORISE
2017-09-15
Patent
Electronic Resource
English