| 摘要 |
The present invention relates to an aircraft comprising a fuselage (1) and a thruster downstream of the fuselage. The thruster includes a power turbine (7), located inside a main flow jet, and at least one fan (9), located inside a secondary flow jet and mechanically driven by the power turbine. The main flow jet of the power turbine and the secondary flow jet of the fan are concentric. The power turbine is supplied with gases from two gas turbine gas generators (3, 5) via two supply channels. Said aircraft is characterized in that said gas turbine gas generators have axes parallel to that of the fuselage. The air inlet sleeve (3A, 5A) is spaced apart from the fuselage, and the supply channels (3C, 5C) each have a hatch (3V, 5V) for controlling the flow between a position for guiding the gas flow to the power turbine and a position for ejecting the gases into the atmosphere while bypassing the power turbine. , |
