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    Assessing Convergence in Predictions of Periodic-Unsteady Flowfields 

    Source: Journal of Turbomachinery:;2007:;volume( 129 ):;issue: 004:;page 740
    Author(s): J. P. Clark; E. A. Grover
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: Predictions of time-resolved flowfields are now commonplace within the gas-turbine industry, and the results of such simulations are often used to make design decisions during the development of ...
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    Predicting Transition in Turbomachinery—Part I: A Review and New Model Development 

    Source: Journal of Turbomachinery:;2007:;volume( 129 ):;issue: 001:;page 1
    Author(s): T. J. Praisner; J. P. Clark
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: Here we report on an effort to include an empirically based transition modeling capability in a Reynolds Averaged Navier-Stokes solver. Well known empirical models for both attached- and ...
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    Turbulent-Spot Propagation in a Decelerating, Compressible Flow 

    Source: Journal of Fluids Engineering:;1996:;volume( 118 ):;issue: 003:;page 612
    Author(s): J. P. Clark; T. V. Jones; J. E. LaGraff
    Publisher: The American Society of Mechanical Engineers (ASME)
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    Predicting Transition in Turbomachinery—Part II: Model Validation and Benchmarking 

    Source: Journal of Turbomachinery:;2007:;volume( 129 ):;issue: 001:;page 14
    Author(s): T. J. Praisner; J. P. Clark; E. A. Grover; M. J. Rice
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: The ability to predict boundary layer transition locations accurately on turbomachinery airfoils is critical both to evaluate aerodynamic performance and to predict local heat-transfer coefficients ...
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    Migration of Combustor Exit Profiles Through High Pressure Turbine Vanes 

    Source: Journal of Turbomachinery:;2009:;volume( 131 ):;issue: 002:;page 21010
    Author(s): M. D. Barringer; M. D. Polanka; J. P. Clark; K. A. Thole; P. J. Koch
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: The high pressure turbine stage within gas turbine engines is exposed to combustor exit flows that are nonuniform in both stagnation pressure and temperature. These highly turbulent flows typically ...
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