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.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Military Specification Effects on Engine Particle Separator Design


    Weitere Titelangaben:

    Sae Technical Papers


    Beteiligte:
    Diehl, Bert A. (Autor:in)

    Kongress:

    Aerospace Technology Conference and Exposition ; 1987



    Erscheinungsdatum :

    1987-10-01




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch





    Gas turbine engine particle separator

    MAYER JEFFERY / ROBERTS BRIAN / ANISKO JONATHAN | Europäisches Patentamt | 2017

    Freier Zugriff

    Inertial particle separator for aircraft engine

    YAN GUORONG / CUNNINGHAM MARK | Europäisches Patentamt | 2022

    Freier Zugriff

    INERTIAL PARTICLE SEPARATOR FOR ENGINE INLET

    BISSON FRANCOIS / CUNNINGHAM MARK | Europäisches Patentamt | 2019

    Freier Zugriff

    INERTIAL PARTICLE SEPARATOR FOR AIRCRAFT ENGINE

    YAN GUORONG / CUNNINGHAM MARK | Europäisches Patentamt | 2023

    Freier Zugriff