Effect of inlet swirl on the performance of annular diffusers having the same equivalent cone angle

    Authors

    S. N. Singh; V. Seshadri; K. Saha; K. K. Vempati;S. Bharani

    Comments

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    Abbreviated Journal Title

    Proc. Inst. Mech. Eng. Part G-J. Aerosp. Eng.

    Keywords

    annular diffuser; gas turbine engine; equivalent cone angle; inlet; swirl; static pressure recovery coefficient; total pressure loss; coefficient; COMPRESSOR EXIT CONDITIONS; COMBUSTOR; FLOW; Engineering, Aerospace; Engineering, Mechanical

    Abstract

    Annular diffusers are an integral component of the gas turbine engines of high-speed aircraft. These facilitate effective operation of the combustor by reducing the total pressure loss. The performance characteristics of these diffusers depend on their geometry and the inlet conditions. The present investigation attempts to select the range of the inlet swirl intensity for the best performance of annular diffusers with different geometries but having the same equivalent cone angle. This is analysed on the basis of the static pressure recovery and total pressure loss coefficients. The results show that the parallel diverging hub and casing annular diffuser produces the best performance at high-swirl intensities.

    Journal Title

    Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering

    Volume

    220

    Issue/Number

    G2

    Publication Date

    1-1-2006

    Document Type

    Article

    Language

    English

    First Page

    129

    Last Page

    143

    WOS Identifier

    WOS:000237821800004

    ISSN

    0954-4100

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