05002993-2718CA 123377CA01 ABSTRACT A feedback device for use in a gas turbine engine, and methods and systems for controlling a pitch for an aircraft-bladed rotor, are provided. The feedback device is composed of a circular disk and a plurality of position markers. The circular disk is coupled to rotate with a rotor of the gas turbine engine, to move along a longitudinal axis of the rotor, and has first and second opposing faces defining a root surface that extends between and circumscribes the first and second faces. The plurality of position markers extend radially from the root surface and are circumferentially spaced around the circular disk. The position markers have a top surface elevated with respect to the root surface and opposing first and second side surfaces. The side surfaces of the position markers have a curved concave profile extending toward the root surface. Date Recue/Date Received 2020-11-12


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    Titel :

    PITCH CONTROL ASSEMBLY FOR AN AIRCRAFT-BLADED ROTOR


    Beteiligte:
    TOMESCU DANA (Autor:in)

    Erscheinungsdatum :

    2021-05-14


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    G01B MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS , Messen der Länge, der Dicke oder ähnlicher linearer Abmessungen / B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / G01D MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE , Anzeigen oder Aufzeichnen in Verbindung mit Messen allgemein



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