| 摘要 |
A multi-shaft aeronautical turboprop engine in which a compressor (4) draws in air coming from an air intake (5) and drives, through an outer first shaft (7), a first stage (8p) of a turbine (8), which is provided with a second stage (8s) that drives a propeller (12) by means of a second shaft (13) mounted coaxially inside the first shaft (7). A starting system is provided that comprises: an asynchronous reversible electric machine (20) connected by means of a transmission (19) to the first shaft (7); a synchronous electric machine (22) connected by means of a transmission (15) to the second shaft (13); a reconfigurable electrical network (25) that, in a phase of dynamic starting of the turboprop engine (1) following its cutting out during flight, enables the transfer of energy produced by the synchronous electric machine (22), set in rotation by the propeller driven by dynamic effects, to the asynchronous electric machine (20), which is set in rotation at a lower speed than the asynchronous machine. The torque generated by the asynchronous machine (20) is added to the torque originating from the blade compressor, which is impinged upon by the airflow coming from the air intake (5); the composition of these torques enables the first shaft (7) to be set in rotation at a speed sufficient to achieve the restarting of the turboprop engine. |
