An engine bleed control system (50) for a gas turbine engine of an aircraft is provided. The engine bleed control system (50) includes a multi-tap bleed array (51) including engine bleed taps (52A-52D) coupled to a compressor source (54) of a lower pressure compressor section before a highest pressure compressor section of the gas turbine engine (10). A highest stage of the engine bleed taps has a maximum bleed temperature below an auto-ignition point of a fuel-air mixture of the aircraft at idle engine power at a maximum aircraft altitude and a pressure suitable for pressurizing the aircraft at the maximum aircraft altitude. The engine bleed control system (50) also includes a plurality of valves (58A-58C) operable to extract bleed air from each of the engine bleed taps (52A-52C). A controller (48) is operable to selectively open and close each of the valves based on a bleed air demand and control delivery of the bleed air to an aircraft use.
ENGINE BLEED SYSTEM WITH MULTI-TAP BLEED ARRAY
MOTORENTLÜFTUNGSSYSTEM MIT ENTLÜFTUNGSANORDNUNG MIT MEHREREN HAHNEN
SYSTÈME DE PURGE DE MOTEUR AVEC RÉSEAU DE PURGE MULTIPRISE
2023-03-01
Patent
Elektronische Ressource
Englisch