| 摘要 |
A turbine engine (1, figure 1) for an aircraft comprises a gas generator (14), a receiver (30) driven by a power turbine 34 and an electric power generator 60. The electric power generator has a rotor 62 having a rotor axis 62' distinct from the longitudinal axis (2) of the turbine engine and is set into rotation by said power turbine. A mechanical transmission 80 with gears connects the power turbine and the rotor wherein the mechanical transmission further comprises a toothed drive wheel 82, centred on the longitudinal axis of the turbine engine. The receiver is provided with a first propeller driven by a first free power turbine the toothed drive wheel being attached on an outer case 40 of said first power turbine. The toothed drive wheel may cooperate with a toothed portion provided on a rotor extension centred on the rotor axis.
|
