A system for ventilating a helicopter engine compartment includes an ejector tube, ambient air inlet(s) and door(s) conjoining the engine compartment. The ejector tube encompasses the engine exhaust pipe mouth and downstream exhaust gas flow for a prescribed distance utilizing the low pressure, high velocity exhaust gases to create a low pressure area around the outer perimeter of the exhaust pipe mouth located in the approximate centre of the ejector tube. This causes the higher pressure engine compartment air to flow into the ejector tube inlet and accelerate downstream to the ejector tube outlet at the approximate velocity of the exhaust gases thereby drawing the heated engine compartment air with it. Ambient air inlets, located at the forward perimeter of the engine compartment provide a means for outside, cooling air to be drawn into the engine compartment to replace the air drawn out of the compartment through the ejector tube. The doors form a continuous seal at all contact points to inhibit random airflow into the engine compartment.


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    Title :

    HELICOPTER ENGINE COMPARTMENT VENTILATING SYSTEM


    Additional title:

    SYSTEME DE VENTILATION DU COMPARTIMENT REACTEUR D`HELICOPTERE


    Contributors:

    Publication date :

    2020-04-09


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01P Kühlung von Kraft- und Arbeitsmaschinen oder Kraftmaschinen allgemein , COOLING OF MACHINES OR ENGINES IN GENERAL



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