A gas turbine engine is defined wherein the inlet guide vanes leading into a core engine flow path are sized and positioned such that flow paths positioned circumferentially intermediate the vane are sufficiently large that a hydraulic diameter of greater than or equal to about 1.5 is achieved. This will likely reduce the detrimental effect of icing.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Anti-icing core inlet stator assembly for a gas turbine engine


    Beteiligte:

    Erscheinungsdatum :

    19.07.2022


    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 / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES



    Anti-icing core inlet stator assembly for a gas turbine engine

    FEULNER MATTHEW R / LIAO SHENGFANG | Europäisches Patentamt | 2016

    Freier Zugriff

    COMPOUND ENGINE ASSEMBLY WITH INLET LIP ANTI-ICING

    LAMARRE SYLVAIN / FONTAINE MIKE / JULIEN ANDRE et al. | Europäisches Patentamt | 2023

    Freier Zugriff

    Gas turbine engine with short inlet, acoustic treatment and anti-icing features

    SCHWARZ FREDERICK M / MURPHY MICHAEL JOSEPH | Europäisches Patentamt | 2020

    Freier Zugriff

    Turbine engine blower module, including a turbine engine inlet cone de-icing system and de-icing method

    KEVIN MORGANE LEMARCHAND / NILS EDOUARD ROMAIN BORDONI / GUILLAUME PATRICE KUBIAK | Europäisches Patentamt | 2021

    Freier Zugriff

    Thermal analysis of engine inlet anti-icing systems

    KEITH, THEO G. / DEWITT, KENNETH J. / NATHMAN, JAMES K. et al. | AIAA | 1990