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.


    Access

    Download


    Export, share and cite



    Title :

    Pitch angles of an aircraft engine rotor assembly



    Publication date :

    2023-11-14


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    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 | European Patent Office | 2024

    Free access

    PITCH BEARING ASSEMBLY FOR ROTOR SYSTEM AND AIRCRAFT

    LEHTO RYAN / HIGBIE ROBERT D / MCCOLLOUGH JAMES EVERETT et al. | European Patent Office | 2018

    Free access

    PITCH CONTROL ASSEMBLY FOR AN AIRCRAFT-BLADED ROTOR

    TOMESCU DANA | European Patent Office | 2024

    Free access

    PITCH CONTROL ASSEMBLY FOR AN AIRCRAFT-BLADED ROTOR

    TOMESCU DANA | European Patent Office | 2022

    Free access

    Pitch control assembly for an aircraft-bladed rotor

    TOMESCU DANA | European Patent Office | 2022

    Free access