A connecting unit 1, for an aircraft, comprising the means to combine the exhaust gases of two or more gas turbine engines 3 (or reaction engines, turbo jet engines, twin engines) to extract energy at a single exhaust. This puts the thrust of the aircraft at the aircrafts centreline, thereby overcoming issues of asymmetric power in the event of redundancy or shutdown, preventing yaw and rolling in the event of an engine shutting down. A gas tight seal is created with the ability to incorporate a turbine 4 to extract energy driven shaft 5 to be connected to either a generator (such as to drive electrical systems), or a propeller or an airscrew and with the ability to incorporate thrust augmentation systems, such as afterburners (6, figure 4), to improve thrust and reduce fuel consumption via the combining of the core flow of the two engines.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Unitary exhaust


    Beteiligte:

    Erscheinungsdatum :

    14.03.2018


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



    Unitary floor

    BANERJEE ROBIN / SHEPPARD MICHAEL S | Europäisches Patentamt | 2019

    Freier Zugriff

    Unitary floor

    BANERJEE ROBIN / SHEPPARD MICHAEL S | Europäisches Patentamt | 2018

    Freier Zugriff

    UNITARY FLOOR

    BANERJEE ROBIN / SHEPPARD MICHAEL S | Europäisches Patentamt | 2017

    Freier Zugriff

    UNITARY FLOOR

    BANERJEE ROBIN / SHEPPARD MICHAEL S | Europäisches Patentamt | 2018

    Freier Zugriff

    Unitary HPAC System

    Kowsky, C. / Leitzel, L. / Oddi, F. et al. | British Library Conference Proceedings | 2012