A cooling system is provided in a hybrid electric propulsion gas turbine engine for cooling electrical components therein. The cooling system includes an electrical component disposed in proximity to a power generation component in the hybrid electric propulsion gas turbine engine. The cooling system further includes a vapor chamber having an evaporator portion and a condenser portion, wherein the evaporator portion is disposed adjacent to and in thermal communication with the electrical component to transfer heat away from the electrical component. The vapor chamber includes biphasic working fluid therein that transitions between liquid and gaseous states as the working fluid flows proximal to the condenser portion and the evaporator portion respectively.


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    Titel :

    Cooling System In A Hybrid Electric Propulsion Gas Turbine Engine For Cooling Electrical Components Therein


    Beteiligte:

    Erscheinungsdatum :

    10.01.2019


    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 / H02K Dynamoelektrische Maschinen , DYNAMO-ELECTRIC MACHINES / H05K PRINTED CIRCUITS , Gedruckte Schaltungen



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