An aircraft propulsion system includes a primary energy conversion device that uses a cryogenic fuel and air to generate power and thermal energy. The primary energy conversion device is mounted to a first structure of an aircraft. A bottoming cycle includes a working fluid that is circulated within a closed circuit that includes a bottoming compressor section and a bottoming turbine section. At least a portion of the bottoming cycle is mounted to a second structure of the aircraft that is different from the first structure. A primary heat exchanger provides communication of thermal energy from the primary conversion device to the working fluid of the bottoming cycle and is mounted within the first structure of the aircraft proximate the primary energy conversion device.


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    Titel :

    MULTIPLE HEAT SOURCE CRYOGENIC BOTTOMING CYCLE SEQUENCING AND ROUTING


    Beteiligte:

    Erscheinungsdatum :

    31.10.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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    EVANS BRANDON M / TERWILLIGER NEIL J | Europäisches Patentamt | 2024

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    STACKED CRYOGENIC BOTTOMING CYCLES

    EVANS BRANDON M / TERWILLIGER NEIL J | Europäisches Patentamt | 2024

    Freier Zugriff

    Organic Rankine Bottoming Cycle

    Doyle,E. / ThermoElectron,US | Kraftfahrwesen | 1976


    Bottoming-Cycle fuer Nutzfahrzeuge

    Henkel, G. / Struck, W. / Moetz, K. | Tema Archiv | 1985