A cooling system for an aircraft comprises a gas turbine engine, an ancillary apparatus, and a heat exchanger. The gas turbine engine comprises, in axial flow sequence, a compressor module, a combustor module, and a turbine module, with a first electric machine being rotationally connected to the turbine module. The first electrical machine is configured to generate an electrical power PEM1 (W). The heat exchanger is configured to transfer a total waste heat energy Q (W) generated by the gas turbine engine and the ancillary apparatus, to an airflow passing through the heat exchanger, and a ratio S of:S=(Total⁢Electrical⁢Power⁢Generated=PEM⁢1)(Total⁢Heat⁢Energy⁢Rejected⁢to⁢Airflow=Q)is in a range of between 0.50 and 5.00.


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    Titel :

    Gas turbine engine with electric machines


    Beteiligte:

    Erscheinungsdatum :

    2024-06-11


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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