An aircraft system is provided that includes a propulsor rotor, a powerplant, a cooling system, an anti-icing system and an aircraft structure. The powerplant is operatively and rotatably coupled to the propulsor rotor. The cooling system includes a cooling circuit and an air duct. The cooling circuit is thermally coupled with the powerplant to extract heat energy from the powerplant. The cooling circuit is thermally coupled with air flowing within the air duct to transfer the heat energy into the air and provide heated air. The anti-icing system includes an inlet fluidly coupled with the air duct. The anti-icing system is adapted to bleed some of the heated air from the air duct through the inlet to provide bleed air. The aircraft structure includes an exterior surface. The anti-icing system is adapted to direct the bleed air into the aircraft structure to heat the exterior surface.


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    Title :

    AIRCRAFT THERMAL ANTI-ICING SYSTEM


    Additional title:

    SYSTEME ANTIGIVRAGE THERMIQUE POUR AERONEF


    Contributors:

    Publication date :

    2024-06-13


    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



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