Military aircraft engine specifications do not explicitly define the required performance characteristics for an inlet protection system. Particle separation efficiency, pressure loss, physical size, weight and cost for this engine component are defined by the engine designer based upon the required environmental ingestion criteria established in the engine specification. The need for an inlet particle separator system is initially created by the requirement for the propulsion system to successfully pass sand and dust ingestion testing. Once the need for an inlet protection system is established it is considered as much a part of the engine as the compressor, combustor, turbines, mechanical components, and the controls and accessories.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Military specification effects on engine particle separator design


    Additional title:

    Auswirkung der militaerischen Spezifikationen auf die Konstruktion des Teilchenabscheiders an Flugzeugmotoren


    Contributors:

    Published in:

    SAE-Papers ; Oct ; 1-7


    Publication date :

    1987


    Size :

    7 Seiten, 4 Bilder, 3 Tabellen, 1 Quelle


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English





    Gas turbine engine particle separator

    MAYER JEFFERY / ROBERTS BRIAN / ANISKO JONATHAN | European Patent Office | 2017

    Free access

    Inertial particle separator for engine inlet

    BISSON FRANCOIS / CUNNINGHAM MARK | European Patent Office | 2019

    Free access

    INERTIAL PARTICLE SEPARATOR FOR TURBINE ENGINE

    MENHEERE DAVID / CHIAPPETTA SANTO / REDFORD TIM et al. | European Patent Office | 2021

    Free access

    Engine inlet with deployable particle separator

    GIANOPULOS ELIA N | European Patent Office | 2022

    Free access