A gas turbine engine comprising a compressor, a compressor case surrounding the compressor and a compressor tip injector system is disclosed. The compressor tip injector system comprises a cabin blower system comprising a cabin blower compressor arranged in use to compress air used in a cabin of an aircraft and by the compressor tip injector system. The compressor case comprises one or more injectors of the compressor tip injector system through which in use air from the cabin blower compressor is injected towards blade tip ends of blades of the compressor as they rotate.
GAS TURBINE WITH COMPRESSOR BLADE TIP INJECTOR
GASTURBINE MIT EINSPRITZDÜSE FÜR VERDICHTERSCHAUFELSPITZE
TURBINE GAZ AVEC INJECTEUR À D'EXTRÉMITÉ DES PALES DE COMPRESSEUR
2016-11-23
Patent
Elektronische Ressource
Englisch
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