A system for supplying pressurized air installed in an aircraft turbine engine, configured to supply pressurization air to a portion of the aircraft for using compressed air from pressurization air collected from a portion for collecting compressed air, characterized in that it comprises a collection port formed on a casing of the compressed air collection portion, a collection member coupled to the collection port, a through port of the collection member formed on a casing of a compartment of the turbine engine, said casing being subjected to small movements relative to the casing of the compressed air portion, the collection member crossing the through port with a freedom of movement relative to the latter during said small movements, a high-pressure space crossed by the collection member, located between the casing of the compressed air collection portion and the casing of the compartment.


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    Titel :

    System for supplying pressured air installed in an aircraft turbine engine including sealing means


    Beteiligte:

    Erscheinungsdatum :

    2018-06-12


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    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 / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS




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