An aircraft with a turbofan engine assembly having at least one compressor, a nacelle surrounding the turbine engine and defining an annular bypass duct between the nacelle and the turbine engine, a thrust reverser having at least one moveable control surface, a thrust reverser locking system configured to selectively lock the thrust reverser and an injection cooling system
AIRCRAFT WITH INJECTION COOLING SYSTEM AND INJECTION COOLING SYSTEM
2017-11-30
Patent
Elektronische Ressource
Englisch
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