A method of bleeding air from a gas turbine engine having a compressor section with a downstream centrifugal compressor is described, which includes bleeding air from a first location upstream of the centrifugal compressor's outlet, when the compressor is operating in a first pressure range, and bleeding air from a second location upstream of the centrifugal compressor's outlet, when the engine is operating in a second pressure range.
GAS TURBINE ENGINE BLEED CONFIGURATION
CONFIGURATION DE PURGE DE MOTEUR DE TURBINE A GAZ
2018-05-14
Patent
Electronic Resource
English
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