An aircraft engine, has: a low-pressure compressor and a high-pressure compressor located downstream of the low-pressure compressor; a gaspath valve upstream of the high-pressure compressor, the gaspath valve movable between an open configuration and a closed configuration; and a bypass flow path having in flow series a bypass inlet, a bypass valve, and a bypass outlet, the bypass inlet fluidly communicating with the gaspath upstream of at least one stage of the low-pressure compressor, the bypass valve having an open configuration in which the bypass valve allows a bypass flow and a closed configuration in which the bypass valve blocks the bypass flow, the bypass outlet fluidly communicating with the bypass inlet via the bypass valve and with the gaspath at a location in the gaspath fluidly downstream of the gaspath valve, downstream of the low-pressure compressor, and upstream of the high-pressure compressor.
GAS TURBINE ENGINE WITH LOW-PRESSURE COMPRESSOR BYPASS
TURBINE A GAZ A DERIVATION DE COMPRESSEUR BASSE PRESSION
2023-01-21
Patent
Elektronische Ressource
Englisch
Gas turbine engine compression system with core compressor pressure ratio
Europäisches Patentamt | 2023
|