All aircraft gas turbine engines currently compromise compression system performance at some point(s) in their operating envelope to obtain 'adequate' stall margin. This work pursues the concept of active stall control to minirnize or eliminate this penalty, thereby improving the performance of any aircraft gas turbine engine.


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    Titel :

    Characterization of Stall Inception in High-Speed Single-Stage Compressors


    Beteiligte:
    K. Boyer (Autor:in)

    Erscheinungsdatum :

    1994


    Format / Umfang :

    166 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch





    Experimental and Theoretical Investigations of Stall Inception in a High-Speed Multi-Stage Compressors

    Escuret, J. F. / Garnier, V. / International Society for Air Breathing Engines; Australian Committee | British Library Conference Proceedings | 1995