A pitch change mechanism (100:200) for a bladed rotor comprises a driving sleeve (110:210), a drive shaft (102:202), a first pitch-changing element (130:230), a second pitch-changing element (150:250), and a plurality of blade drive gears (180). The driving sleeve (110:210) has, in axial sequence, a first helical connection portion (133:233) and a second helical connection portion (153:253). The driving sleeve (110:210) is positioned concentrically with and surrounding the drive shaft (102:202). The first pitch-changing element (130:230) has a first end (132:232) drivingly engaged with the first helical connection portion (133:233), and a first ring gear portion (140:240) at a second opposite end (138:238), while the second pitch-changing element (150:250) has a first end (152:252) drivingly engaged with the second helical connection portion (153:253), and a second ring gear portion (160:260) at a second opposite end (158:258). The plurality of blade drive gears (180) are arranged in a circumferential array around a longitudinal axis of the drive shaft (102:202). The first pitch-changing element (130:230) is positioned axially adjacent to the second pitch-changing element (150:250) with the first ring gear portion (140:240) facing the second ring gear portion (160:260). Each of the first and second pitch-changing elements (130:230,150:250) is positioned concentrically over the driving sleeve (110:210), such that axial movement of the driving sleeve (110:210) causes the first helical connection portion (133:233) to rotate the first pitch-changing element (130:230) in a first rotational direction (144), and simultaneously causes the second helical connection portion (153:253) to rotate the second pitch-changing element (150:250) in an opposite second rotational direction (164), with the contra-rotation of the first and second pitch-changing elements (130:230,150:250) causing a rotation of the plurality of blade drive gears (180) positioned between and meshingly coupled to each of the first ring gear portion (140:240) and the second ring gear portion (160:260).


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    A PITCH CHANGE MECHANISM FOR A BLADED ROTOR


    Weitere Titelangaben:

    MECHANISMUS ZUR ÄNDERUNG DER STEIGUNG FÜR EINEN BESCHAUFELTEN ROTOR
    MÉCANISME DE CHANGEMENT DE PAS POUR ROTOR DE SOUFFLANTE


    Beteiligte:
    CURNOCK PHILIP (Autor:in) / DI MARTINO MARIO (Autor:in)

    Erscheinungsdatum :

    2017-03-15


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES



    PITCH CHANGE MECHANISM FOR A BLADED ROTOR

    CURNOCK PHILIP A / DI MARTINO MARIO | Europäisches Patentamt | 2017

    Freier Zugriff

    Pitch change mechanism for a bladed rotor

    CURNOCK PHILIP A / DI MARTINO MARIO | Europäisches Patentamt | 2019

    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 | 2022

    Freier Zugriff

    Pitch control assembly for an aircraft-bladed rotor

    TOMESCU DANA | Europäisches Patentamt | 2022

    Freier Zugriff