A small, two-stage, transonic axial compressor was selected for a 5 lb/s airflow, 0.46 lb/hp · h, sfc turboshaft engine at 2500 F turbine-inlet gas temperature. The axial compressor was configured to supercharge a single-stage centrifugal compressor to provide an overall axial/centrifugal pressure ratio of 16:1.The axial compressor was designed, fabricated, and developed through rig testing. On final test, a pressure ratio of 3.1:1 was demonstrated at 80% efficiency with 10% surge margin.


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    Titel :

    Design and Development of a Small Highly Loaded, Two-Stage, Transonic Axial Compressor


    Weitere Titelangaben:

    Sae Technical Papers


    Beteiligte:
    Davis, J. V. (Autor:in)

    Kongress:

    National Farm, Construction, Industrial Machinery, Powerplant Meeting ; 1972



    Erscheinungsdatum :

    01.02.1972




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :




    THE COMBINED TRANSONIC AXIAL AND CENTRIFUGAL STAGE COMPRESSOR

    RAHNKE, C. J. / CARMODY, R. H. | SAE Technical Papers | 1961


    Analysis of a Highly Loaded, Transonic, Inlet Compressor Stage: Isolated and Multi-stage Performance

    Car, D. / Puterbaugh, S. L. / Chriss, R. M. et al. | British Library Conference Proceedings | 2000