A thermal management system for an aircraft is provided. The thermal management system may comprise a first vapor compression circuit, a second vapor compression circuit, and an intercooler. The first vapor compression circuit may define a first flowpath for fluid compression, condensation, expansion, and evaporation. The second vapor compression circuit may define a second flowpath for fluid compression, condensation, expansion, and evaporation. The intercooler may be disposed in cascading thermal communication between the first vapor compression circuit and the second vapor compression circuit. Generally, heat generated by the aircraft may be transferred to the first vapor compression circuit during aircraft operation.


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    Title :

    Aircraft Thermal Management System


    Contributors:

    Publication date :

    2017-08-03


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F25B Kältemaschinen, Kälteanlagen oder Kälteverfahren , REFRIGERATION MACHINES, PLANTS, OR SYSTEMS



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