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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    Title :

    Cooling system in a hybrid electric propulsion gas turbine engine for cooling electrical components therein


    Contributors:

    Publication date :

    2021-03-02


    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 / F02K JET-PROPULSION PLANTS , Strahltriebwerke / H02K Dynamoelektrische Maschinen , DYNAMO-ELECTRIC MACHINES / H05K PRINTED CIRCUITS , Gedruckte Schaltungen



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