A thermal management system for one or more aircraft components includes a bleed airflow source at a gas turbine engine (20) of the aircraft, one or more turbines (68) configured to expand the bleed airflow, thus lowering a temperature of the bleed airflow, the bleed airflow driving rotation of the one or more turbines. One or more heat exchangers (70) are in fluid communication with the one or more turbines. The one or more heat exchangers are configured to exchange thermal energy between the bleed airflow and a thermal load. One or more electrical generators (94) are operably connected to the one or more turbines. The one or more electrical generators are configured to convert rotational energy of the one or more turbines to electrical energy.


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    Title :

    THERMAL MANAGEMENT SYSTEM WITH COOLING TURBINE AND GENERATOR


    Additional title:

    WÄRMEVERWALTUNGSSYSTEM MIT KÜHLTURBINE UND GENERATOR
    SYSTÈME DE GESTION THERMIQUE AVEC TURBINE DE REFROIDISSEMENT ET GÉNÉRATEUR


    Contributors:
    BARTOSZ LANCE R (author) / HO TONY (author) / RETERSDORF ALAN (author) / PESS MATTHEW (author)

    Publication date :

    2023-05-03


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



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