TY - GEN
T1 - Three-dimensional navier-stokes computation of turbomachinery flows using an explicit numerical procedure and a coupled κ-ε turbulence model
AU - Kunz, R. F.
AU - Lakshminarayana, B.
N1 - Publisher Copyright:
Copyright © 1991 by ASME.
PY - 1991
Y1 - 1991
N2 - An explicit, three-dimensional, coupled Navier-Stokes/κ-ε technique has been developed and successfully applied to complex internal flow calculations. Several features of the procedure, which enable convergent and accurate calculation of high Reynolds number twodimensional cascade flows have been extended to three-dimensions, including a low Reynolds number compressible form of the κ-ε turbulence model, local timestep specification based on hyperbolic and parabolic stability requirements, and eigenvalue and local velocity scaling of artificial dissipation operators. A flux evaluation procedure which eliminates the finite difference metric singularity, at leading and trailing edges, on H- And C-grids, is presented. The code is used to predict the pressure distribution, primary velocity and secondary flows in an incompressible, turbulent curved duct flow for which CFD validation quality data is available. Also, a subsonic compressor rotor passage, for which detailed laser, rotating hot-wire and five-hole pressure probe measurements have been made is computed. Detailed comparisons between predicted and measured core flow and near wall velocity profiles, wake profiles, and spanwise mixing effects downstream of the rotor passage are presented for this case. It is found that the technique provides accurate and convergent engineering simulation of these complex turbulent flows.
AB - An explicit, three-dimensional, coupled Navier-Stokes/κ-ε technique has been developed and successfully applied to complex internal flow calculations. Several features of the procedure, which enable convergent and accurate calculation of high Reynolds number twodimensional cascade flows have been extended to three-dimensions, including a low Reynolds number compressible form of the κ-ε turbulence model, local timestep specification based on hyperbolic and parabolic stability requirements, and eigenvalue and local velocity scaling of artificial dissipation operators. A flux evaluation procedure which eliminates the finite difference metric singularity, at leading and trailing edges, on H- And C-grids, is presented. The code is used to predict the pressure distribution, primary velocity and secondary flows in an incompressible, turbulent curved duct flow for which CFD validation quality data is available. Also, a subsonic compressor rotor passage, for which detailed laser, rotating hot-wire and five-hole pressure probe measurements have been made is computed. Detailed comparisons between predicted and measured core flow and near wall velocity profiles, wake profiles, and spanwise mixing effects downstream of the rotor passage are presented for this case. It is found that the technique provides accurate and convergent engineering simulation of these complex turbulent flows.
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U2 - 10.1115/91-GT-146
DO - 10.1115/91-GT-146
M3 - Conference contribution
AN - SCOPUS:84924788148
T3 - Proceedings of the ASME Turbo Expo
BT - Turbomachinery
PB - American Society of Mechanical Engineers (ASME)
T2 - ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition, GT 1991
Y2 - 3 June 1991 through 6 June 1991
ER -