The patent relates to a transition of improved design for joining the merging surfaces of the airfoil and platform of an axial-flow compressor blade of the cantilevered type. The transition as viewed in profile is a line comprising an essentially straight major portion diverging outwardly from and faired into the airfoil and an outwardly concave minor portion extending along and faired into the platform.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Blade Transition for Axial-Flow Compressors and the Like


    Beteiligte:
    D. E. Hendriz (Autor:in) / R. E. Ziegler (Autor:in) / W. E. Swinson (Autor:in)

    Erscheinungsdatum :

    1972


    Format / Umfang :

    7 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Flow Phenomena Inside the Rotor Blade Passages of Axial Compressors

    Muller, R. / Mailach, R. / Lehman, I. et al. | British Library Conference Proceedings | 1999



    Stall propagation in axial-flow compressors

    Stenning, A.H. / Kriebel, A.R. / Montgomery, S.R. | Engineering Index Backfile | 1956


    Axial Flow Compressors - Mechanical Design Trends

    Geidel, H. A. / Zahring, G. / Lottes, P. et al. | British Library Conference Proceedings | 1993


    Aerodynamic Design of Axial-Flow Compressors

    Irving A Johnson / Robert O Bullock | NTRS | 1965