An inlet guide vane assembly for an aircraft engine includes an array of inlet guide vanes having radially inner ends at a radially inner shroud, radially outer ends at a radially outer shroud, and airfoils extending therebetween. An internal passage extends radially through the airfoil from a vane air inlet at the radially inner end to a vane air outlet at the radially outer end. The vane air inlet is in fluid communication with an inner plenum, disposed radially inwardly of the inlet guide vane and in fluid communication with an anti-icing air source. The vane air outlet in fluid communication with an outer plenum, disposed radially outwardly of the inlet guide vane and having an exhaust port. A vane anti-icing pathway is defined in a radially-outward direction from the inner plenum, through the internal passage of the vane, and into the outer plenum.


    Access

    Download


    Export, share and cite



    Title :

    SYSTEM AND METHOD OF ANTI-ICING INLET GUIDE VANES


    Additional title:

    SYSTEME ET METHODE D'AUBAGES DIRECTEURS D'ENTREE D'ANTIGIVRANT


    Contributors:

    Publication date :

    2023-11-10


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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





    Experimental Study of an Anti-Icing System for Stator and Inlet Guide Vanes

    Tetteh, Edem / Stebbins, Spencer J. / Spivey, Watson et al. | AIAA | 2017


    Variable inlet guide vanes

    European Patent Office | 2023

    Free access

    An Experimental Study on a Hot-Air-Based Anti-/De-Icing System for the Icing Protection of Aero-Engine Inlet Guide Vanes

    Li, Linkai / Tian, Linchuan / Liu, Yang et al. | British Library Conference Proceedings | 2019