An assembly is provided for an aircraft propulsion system. This assembly includes a propulsion module, a gas generator and an anti-icing system. The propulsion module includes an open propulsor rotor. The gas generator is configured to drive rotation of the open propulsor rotor about an axis. The gas generator includes a flowpath, a compressor section, a combustor section, a turbine section and an exhaust section. The flowpath extends through the compressor section, the combustor section, the turbine section and the exhaust section. The turbine section is axially between the combustor section and the open propulsor rotor along the axis. The anti-icing system is configured to bleed gas from the flowpath in the exhaust section to provide heated gas. The anti-icing system is configured to direct the heated gas to the propulsion module to reduce or prevent ice accumulation on an exterior surface of the propulsion module.


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    Title :

    OPEN ROTOR AIRCRAFT PROPULSION SYSTEM WITH ANTI-ICING SYSTEM


    Contributors:

    Publication date :

    2025-06-19


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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