An assembly for an aircraft propulsion system (20) includes a propulsion module (24), a gas generator (26) and an anti-icing system (28). The propulsion module (24) includes an open propulsor rotor (30). The gas generator (26) is configured to drive rotation of the open propulsor rotor (30) and includes a flowpath (74), a compressor section (69), a combustor section (70), a turbine section (71) and an exhaust section (72). The flowpath (74) extends through the compressor section (69), the combustor section (70), the turbine section (71) and the exhaust section (72). The turbine section (71) is axially between the combustor section (70) and the open propulsor rotor (30) along the axis (22). The anti-icing system (28) is configured to bleed gas from the flowpath (74) in the exhaust section (72) to provide heated gas and to direct the heated gas to the propulsion module (24) to reduce or prevent ice accumulation on an exterior surface (50, 66, 108) of the propulsion module (24).


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    Titel :

    OPEN ROTOR AIRCRAFT PROPULSION SYSTEM WITH ANTI-ICING SYSTEM


    Weitere Titelangaben:

    ANTRIEBSSYSTEM FÜR EIN FLUGZEUG MIT OFFENEM ROTOR UND ENTEISUNGSSYSTEM
    SYSTÈME DE PROPULSION D'AÉRONEF À ROTOR OUVERT AVEC SYSTÈME ANTI-GIVRAGE


    Beteiligte:
    SOBANSKI JON E (Autor:in) / MORTON JEFFREY T (Autor:in) / BREAULT ANDREW E (Autor:in)

    Erscheinungsdatum :

    18.06.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES



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