The combined cooling system uses a single heat exchanger to cool both engine air for use in an engine system and aircraft air for use in an aircraft system. More particularly, a bleed air path leads from the compressor stage to the heat exchanger where it is placed in thermal exchange contact with a flow of cooling air coming from a cooling path. From an outlet end of the heat exchanger, the bleed air splits into two paths: an aircraft air path leading to at least one aircraft system such as an Environmental control system (ECS), a wind de-icing system or the like, and an engine air path leading to at least one engine system such as a buffer air system for pressurizing the bearing cavities.


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    Title :

    Cooling system for engine and aircraft air


    Contributors:
    STRECKER STEVEN (author) / LIU XIAOLIU (author) / LOGAN ADAM (author)

    Publication date :

    2016-01-19


    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



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