SYSTEM FOR IN-FLIGHT RESTARTING OF A MULTI-SHAFT TURBOPROP ENGINE

A multi-shaft aeronautical turboprop engine in which a compressor draws in air coming from an air intake and drives, through an outer first shaft, a first stage of a turbine, which is provided with a second stage that drives a propeller by means of a second shaft mounted coaxially inside the first s...

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Bibliographische Detailangaben
Hauptverfasser:	CUOMO FABRIZIO, ANASTASIO VINCENZO
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORSOR DYNAMO-ELECTRIC CONVERTERS CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS CONVERSION OR DISTRIBUTION OF ELECTRIC POWER ELECTRICITY ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS GENERATION HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STARTING AIDS FOR SUCH ENGINES, NOT OTHERWISE PROVIDEDFOR STARTING OF COMBUSTION ENGINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A multi-shaft aeronautical turboprop engine in which a compressor draws in air coming from an air intake and drives, through an outer first shaft, a first stage of a turbine, which is provided with a second stage that drives a propeller by means of a second shaft mounted coaxially inside the first shaft. A starting system. is provided that comprises: an asynchronous reversible electric machine connected by means of a transmission to the first shaft; a synchronous electric machine connected by means of a transmission to the second shaft; a reconfigurable electrical network that, in a phase of dynamic starting of the turboprop engine following its cutting out during flight, enables the transfer of energy produced by the synchronous electric machine, set in rotation by the propeller driven by dynamic effects, to the asynchronous electric machine, which is set in rotation at a lower speed than the asynchronous machine. The torque generated by the asynchronous machine is added to the torque originating from the blade compressor, which is impinged upon by the airflow coming from the air intake; the composition of these torques enables the first shaft to be set in rotation at a speed sufficient to achieve the restarting of the turboprop engine.