A turbine engine system includes aircraft systems including at least one hydrogen fuel tank, engine systems comprising a compressor section, a combustor section having a burner, and a turbine section, and a hydrogen fuel flow supply line configured to supply hydrogen fuel from the at least one hydrogen fuel tank into the burner for combustion. The turbine engine system has a bypass ratio between 5 to 20.


    Access

    Download


    Export, share and cite



    Title :

    HYDROGEN POWERED GEARED TURBOFAN ENGINE WITH REDUCED SIZE CORE ENGINE


    Contributors:

    Publication date :

    2023-01-12


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



    GEARED TURBOFAN ENGINE

    BREEN CLIVE | European Patent Office | 2020

    Free access

    Geared turbofan engine

    BREEN CLIVE | European Patent Office | 2021

    Free access

    Geared turbofan engine mount arrangement

    COLES DAVID R / ROWNTREE GAVIN M / WILLSHEE MATTHEW J et al. | European Patent Office | 2022

    Free access

    Geared Turbofan Engine Mount Arrangement

    COLES DAVID R / ROWNTREE GAVIN M / WILLSHEE MATTHEW J et al. | European Patent Office | 2019

    Free access

    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE

    KUPRATIS DANIEL BERNARD / SCHWARZ FREDERICK M | European Patent Office | 2020

    Free access