An aircraft gas turbine includes a combustor that combusts compressed air and at least one fuel flow from at least one fuel source to generate combustion gases. A fuel supply system is arranged to provide at least one of a first flow of fuel to the combustor via a first fuel supply line and a second flow of a heated fuel to the combustor via a second fuel supply line. A fuel heat exchanger is arranged within the fuel supply system to generate the heated fuel that is heated above an autoignition temperature of the fuel, and a heat source communicates with the fuel heat exchanger for generating the heated fuel.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Aircraft gas turbine engine with heated fuel to assist combustion


    Beteiligte:

    Erscheinungsdatum :

    04.03.2025


    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



    AIRCRAFT GAS TURBINE ENGINE WITH HEATED FUEL TO ASSIST COMBUSTION

    MILLER BRANDON W / NIERGARTH DANIEL A / SIBBACH ARTHUR W | Europäisches Patentamt | 2025

    Freier Zugriff

    INCREASING FUEL COMBUSTION IN AIRCRAFT ENGINE

    NAGORNYJ VLADIMIR STEPANOVICH / KOLODJAZHNYJ DMITRIJ JUR EVICH | Europäisches Patentamt | 2015

    Freier Zugriff

    Aircraft fuel system for gas turbine engine

    BEMMENT CRAIG W / KEELER BENJAMIN J / FERRA PAUL W et al. | Europäisches Patentamt | 2023

    Freier Zugriff

    Turbine engine assembly and dual fuel aircraft system

    WOLLENWEBER GARY CRAIG | Europäisches Patentamt | 2017

    Freier Zugriff

    INTERNAL COMBUSTION ENGINE START ASSIST MECHANISM

    KATSURA SEISHI / KITAMURA TAICHI | Europäisches Patentamt | 2018

    Freier Zugriff