A nacelle assembly for a high-bypass gas turbine engine includes a fan variable area nozzle movable relative a fan nacelle to vary a fan nozzle exit area to reduce a fan instability.
Gas turbine engine with fan variable area nozzle to reduce fan instability
2019-01-01
Patent
Elektronische Ressource
Englisch
IPC: | F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS |
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