A system (300) is provided in one example embodiment and may include a first reservoir (312, 612, 712, 812, 912, 1012) for a lubricant (317); a second reservoir (314, 614, 714, 814, 914, 1014) for the lubricant (317), wherein the first reservoir (312, 612, 712, 812, 912, 1012) and the second reservoir (314, 614, 714, 814, 914, 1014) are interconnected; a first pumping element (304) to pump the lubricant (317) from the first reservoir (312, 612, 712, 812, 912, 1012) at a first flow rate; a second pumping element (306) to pump the lubricant (317) at a second flow rate, wherein the first flow rate and the second flow rate are different; and a gearbox (308) coupled to the first pumping element (304) and the second pumping element (306). The first reservoir (312, 612, 712, 812, 912, 1012) may have a larger volume than the second reservoir (314, 614, 714, 814, 914, 1014) and the first flow rate may be higher than the second flow rate.


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    Titel :

    AIRCRAFT LUBRICATION SYSTEM


    Weitere Titelangaben:

    FLUGZEUGSCHMIERSYSTEM
    SYSTÈME DE LUBRIFICATION D'AÉRONEF


    Beteiligte:
    OLSON ERIC S (Autor:in) / BOCKMILLER DAVID R (Autor:in)

    Erscheinungsdatum :

    2022-03-09


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F16H Getriebe , GEARING / B64C AEROPLANES , Flugzeuge



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