A gas turbine engine for mounting to an airframe of an aircraft comprises an engine core; a fan located upstream of the engine core; a bifurcation spanning a bypass duct defined between the engine core and a nacelle surrounding the gas turbine engine, the bifurcation comprising aerodynamically shaped fairings defining an interior space therebetween; and a cabin blower system arranged in the interior space of the upper bifurcation.
GAS TURBINE ENGINE WITH CABIN BLOWER SYSTEM
2022-05-05
Patent
Elektronische Ressource
Englisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |