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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    Title :

    AIRCRAFT LUBRICATION SYSTEM


    Additional title:

    FLUGZEUGSCHMIERSYSTEM
    SYSTÈME DE LUBRIFICATION D'AÉRONEF


    Contributors:

    Publication date :

    2022-03-09


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F16H Getriebe , GEARING / B64C AEROPLANES , Flugzeuge



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