A method of operating an aircraft engine coupled to a wing of an aircraft including: setting a pitch of a plurality of rotor blades of a rotor assembly of the aircraft engine at non-uniform pitch angles along a circumferential direction of the aircraft engine such that the plurality of rotor blades define a first pitch at a first position and a second pitch at a second position, wherein the second position is 180 degrees offset from the first position, and wherein the first pitch is different from the second pitch.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Pitch angles of an aircraft engine rotor assembly


    Beteiligte:

    Erscheinungsdatum :

    14.11.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES



    PITCH CONTROL ASSEMBLY FOR AN AIRCRAFT-BLADED ROTOR

    TOMESCU DANA | Europäisches Patentamt | 2024

    Freier Zugriff

    PITCH BEARING ASSEMBLY FOR ROTOR SYSTEM AND AIRCRAFT

    LEHTO RYAN / HIGBIE ROBERT D / MCCOLLOUGH JAMES EVERETT et al. | Europäisches Patentamt | 2018

    Freier Zugriff

    Pitch control assembly for an aircraft-bladed rotor

    TOMESCU DANA | Europäisches Patentamt | 2022

    Freier Zugriff

    PITCH CONTROL ASSEMBLY FOR AN AIRCRAFT-BLADED ROTOR

    TOMESCU DANA | Europäisches Patentamt | 2021

    Freier Zugriff

    PITCH CONTROL ASSEMBLY FOR AN AIRCRAFT-BLADED ROTOR

    TOMESCU DANA | Europäisches Patentamt | 2024

    Freier Zugriff