A turbine engine assembly having a turbine core with a compressor section, a combustion section, a turbine section, and a nozzle section and a liquid natural gas (LNG) fuel system having a LNG reservoir, a vaporizer heat exchanger, a first liquid supply line operably coupling the LNG reservoir to an input of the vaporizer heat exchanger, a gas supply line operably coupling an output of the vaporizer heat exchanger to the combustion section, a second liquid supply line operably coupling the LNG reservoir to the gas supply line and a thermostatic expansion valve (TEV) and a dual fuel aircraft control system.


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    Titel :

    Turbine engine assembly and dual fuel aircraft system


    Beteiligte:

    Erscheinungsdatum :

    04.07.2017


    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 / F23K Brennstoffzufuhr zu Feuerungen , FEEDING FUEL TO COMBUSTION APPARATUS / F23R Erzeugen von Verbrennungsprodukten hohen Druckes oder hoher Geschwindigkeit, z.B. Gasturbinenbrennkammern , GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS



    Dual Cycle Aircraft Turbine Engine

    M. R. Nichols | NTIS | 1973


    Dual cycle aircraft turbine engine

    Nichols, M. R. | NTRS | 1977


    Dual Cycle Aircraft Turbine Engine

    M. R. Nichols | NTIS | 1973


    Aircraft fuel system for gas turbine engine

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

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