An auxiliary power unit (10) for an aircraft includes a rotary intermittent internal combustion engine (12) drivingly engaged to an engine shaft (16), a turbine section having an inlet in fluid communication with an outlet of the engine(s) (12), the turbine section including at least one turbine (22, 26) compounded with the engine shaft (16), and a compressor (20) having an inlet in fluid communication with an environment of the aircraft and an outlet in fluid communication with a bleed duct (72) for providing bleed air to the aircraft, the compressor (20) having a compressor rotor connected to a compressor shaft (24), the compressor shaft (24) drivingly engaged to the engine shaft (16). The driving engagement between the compressor shaft (24) and the engine shaft (16) is configurable to provide at least two alternate speed ratios between the compressor shaft (24) and the engine shaft (16).


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    Titel :

    AUXILIARY POWER UNIT WITH VARIABLE SPEED RATIO


    Weitere Titelangaben:

    HILFSGENERATOR MIT VERÄNDERLICHEM DREHZAHLVERHÄLTNIS
    UNITÉ DE PUISSANCE AUXILIAIRE AVEC RAPPORT DE VITESSE VARIABLE


    Beteiligte:
    JONES ANTHONY (Autor:in) / JULIEN ANDRE (Autor:in) / MENHEERE DAVID (Autor:in) / THOMASSIN JEAN (Autor:in) / ULLYOTT RICHARD (Autor:in) / VAN DEN ENDE DANIEL (Autor:in)

    Erscheinungsdatum :

    20.02.2019


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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