The invention relates to an aircraft propelled by a turbojet engine (10) with contrarotating fans, the turbojet engine being incorporated into the rear of a fuselage (2) of the aircraft in the continuation thereof and comprising two gas generators (12a, 12b) powering a working turbine (14) having two contrarotating turbine rotors (14a, 14b) for driving two fans (20a, 20b) positioned downstream of the gas generators, and separate air inlets (18a, 18b) to feed each gas generator, said air inlets being connected to the fuselage of the aircraft in order to absorb at least part of the boundary layer formed around the aircraft fuselage.
Aircraft propelled by a turbojet engine with contrarotating fans
15.07.2015
Patent
Elektronische Ressource
Englisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F23R Erzeugen von Verbrennungsprodukten hohen Druckes oder hoher Geschwindigkeit, z.B. Gasturbinenbrennkammern , GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS |
AIRCRAFT PROPELLED BY A TURBOJET ENGINE WITH CONTRAROTATING FANS
Europäisches Patentamt | 2015
|Aircraft propelled by a turbojet engine with contrarotating fans
Europäisches Patentamt | 2019
|AIRCRAFT WITH TURBOJET ENGINE WITH OPPOSITE ROTATION FANS
Europäisches Patentamt | 2018
|Turbojet engine with offset fans with a diffrential system
Europäisches Patentamt | 2017
|