A Constant Volume Combustion Cycle Engine concept consisting of a Pulse Detonation Combustor (PDC) followed by a conventional axial turbine was simulated numerically to determine the attenuation and reflection of a notional PDC pulse by the turbine. The multi-stage, time-accurate, turbomachinery solver TURBO was used to perform the calculation. The solution domain consisted of one notional detonation tube coupled to 5 vane passages and 8 rotor passages representing 1/8th of the annulus. The detonation tube was implemented as an initial value problem with the thermodynamic state of the tube contents, when the detonation wave is about to exit, provided by a 1D code. Pressure time history data from the numerical simulation was compared to experimental data from a similar configuration to verify that the simulation is giving reasonable results. Analysis of the pressure data showed a spectrally averaged attenuation of about 15 dB across the turbine stage. An evaluation of turbine performance is also presented.


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    Titel :

    The Attenuation of a Detonation Wave by an Aircraft Engine Axial Turbine Stage


    Beteiligte:
    VanZante, Dale (Autor:in) / Envia, Edmane (Autor:in) / Turner, Mark G. (Autor:in)

    Kongress:

    18th ISABE Conference (ISABE 2007) ; 2007 ; Beijing, China


    Erscheinungsdatum :

    01.09.2007


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


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    Numerical Study on Single-Stage Axial Turbine with Pulse Detonation Combustor

    Nango, A. / Inaba, K. / Kojima, T. et al. | British Library Conference Proceedings | 2009


    Numerical Study on Single-Stage Axial Turbine with Pulse Detonation Combustor

    Nango, Ayaka / Inaba, Kazuaki / Kojima, Takayuki et al. | AIAA | 2009


    Numerical Study of Detonation Interaction with a Single-Stage Axial Turbine

    Nango, Ayaka / Inaba, Kazuaki / Kojima, Takayuki et al. | AIAA | 2008