A conceptual design of an afterburner system for turbojet engines which may reduce the jet exhaust noise by approximately 10 decibels is presented in this report. The proposed system consists of an array of swirl-can combustors and jet dividing nozzle tubes. The nozzle tubes translate axially upstream of the swirl cans when not in use. Results of preliminary design calculations and photographs of a kinematic model as applied to a hypothetical turbojet engine are presented. (Author)


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    Title :

    A Concept for Jet Noise Suppression for an Afterburning Turbojet Engine


    Contributors:

    Publication date :

    1972


    Size :

    19 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English