An anti-icing exhaust system for an inlet of a gas turbine engine is provided. The system includes a first housing portion that at least partially defines a chamber to receive an anti-icing fluid and includes a projection. A second housing portion includes a leading edge. The system includes a support structure that couples the first housing portion to the second housing portion such that the projection of the first housing portion is spaced apart from the leading edge of the second housing portion to define a gap. The gap is in fluid communication with a manifold. The support structure defines at least one flow passage in fluid communication with the chamber and the manifold to exhaust the fluid. The system includes an insulation strip having a first end received in the gap and coupled to the leading edge; and a second end coupled to the second housing portion.


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    Titel :

    Anti-icing exhaust system


    Beteiligte:

    Erscheinungsdatum :

    05.03.2019


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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