A propulsion system for an aircraft includes an intercooling system with a plurality of injectors for injecting an intercooling waterflow into a portion of a compressor passage. The plurality of injectors are spaced apart about the compressor passage and the injection of the intercooling water flow is varied between the plurality of injectors to influence flow that is communicated through the compressor passage.


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    Titel :

    Fluidic compressor inlet guide vanes


    Beteiligte:

    Erscheinungsdatum :

    05.11.2024


    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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