A fan for a gas turbine engine comprises blades distributed around a hub. The blades include first and second blades, having geometric parameters and/or material properties that differ from each other to frequency mistune the fan. The blades are distributed about the hub with at least one second blade between adjacent first blades. The leading edge of the airfoil of the second blades is disposed axially aft of the corresponding leading edge of the first blades in at least a portion of the blade span.


    Access

    Download


    Export, share and cite



    Title :

    Mistuned fan for gas turbine engine


    Contributors:

    Publication date :

    2020-11-17


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B63H Schiffsantrieb oder Steuerung der Schiffe , MARINE PROPULSION OR STEERING / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS



    Dynamics of mistuned radial turbine wheels

    Sheng, X. / Clay, D. C. / Allport, J. et al. | British Library Conference Proceedings | 2006



    Multistage coupling of mistuned aircraft engine bladed disks in a free vibration analysis

    Rzadkowski, Romuald / Maurin, Artur / Drewczynski, Marcin | Tema Archive | 2013



    Experimental investigation on forced response of mistuned bladed disc rotor in an aero-engine

    Madhavan, S / Jain, Rajeev / Sujatha, C et al. | SAGE Publications | 2015