An active clearance control system was developed which reduces fuel consumption and performance degradation. This system utilizes compressor discharge air during takeoff and fan discharge air during cruise to impinge on the shroud structure to improve the thermal response. The system was evaluated in component and engine tests. The test results demonstrated a performance improvement of 0.7 percent in cruise SFC.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    CF6 Jet Engine Performance Improvement: High Pressure Turbine Active Clearance Control


    Beteiligte:
    Rich, S. E. (Autor:in) / Fasching, W. A. (Autor:in)

    Erscheinungsdatum :

    01.06.1982


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Gas turbine engine turbine blade tip active clearance control system and method

    TILLMAN DON / GAGE RAYMOND / BARRETT RICH | Europäisches Patentamt | 2016

    Freier Zugriff


    GAS TURBINE ENGINE ACTIVE CLEARANCE CONTROL SYSTEM USING INLET PARTICLE SEPARATOR

    EASTWOOD JONATHAN JEFFERY / ENGLEHART JOSEPH F / PHILBRICK GRAHAM RYAN et al. | Europäisches Patentamt | 2019

    Freier Zugriff

    Gas turbine engine active clearance control system using inlet particle separator

    EASTWOOD JONATHAN JEFFERY / ENGLEHART JOSEPH F / PHILBRICK GRAHAM RYAN et al. | Europäisches Patentamt | 2020

    Freier Zugriff

    TURBINE ENGINE TIP CLEARANCE CONTROL UTILIZING ELECTRIC MACHINE

    PHILBRICK GRAHAM R / COLLOPY GARY / VIRTUE JR JOHN P | Europäisches Patentamt | 2025

    Freier Zugriff