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Comparison of Predicted and Measured Turbine Vane Rough Surface Heat TransferThe proposed paper compares predicted turbine vane heat transfer for a rough surface over a wide range of test conditions with experimental data. Predictions were made for the entire vane surface. However, measurements were made only over the suction surface of the vane, and the leading edge region of the pressure surface. Comparisons are shown for a wide range of test conditions. Inlet pressures varied between 3 and 15 psia, and exit Mach numbers ranged between 0.3 and 0.9. Thus, while a single roughened vane was used for the tests, the effective rougness,(k(sup +)), varied by more than a factor of ten. Results were obtained for freestream turbulence levels of 1 and 10%. Heat transfer predictions were obtained using the Navier-Stokes computer code RVCQ3D. Two turbulence models, suitable for rough surface analysis, are incorporated in this code. The Cebeci-Chang roughness model is part of the algebraic turbulence model. The k-omega turbulence model accounts for the effect of roughness in the application of the boundary condition. Roughness causes turbulent flow over the vane surface. Even after accounting for transition, surface roughness significantly increased heat transfer compared to a smooth surface. The k-omega results agreed better with the data than the Cebeci-Chang model. However, the low Reynolds number k-omega model did not accurately account for roughness when the freestream turbulence level was low. The high Reynolds number version of this model was more suitable when the freestream turbulence was low.
Document ID
20010017164
Acquisition Source
Glenn Research Center
Document Type
Preprint (Draft being sent to journal)
Authors
Boyle, R. J. (NASA Glenn Research Center Cleveland, OH United States)
Spuckler, C. M. (NASA Glenn Research Center Cleveland, OH United States)
Lucci, B. L. (NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
September 7, 2013
Publication Date
December 1, 2000
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
E-12338
ASME-2000-GT-0217
NASA/TM-2000-210219
NAS 1.15:210219
Report Number: E-12338
Report Number: ASME-2000-GT-0217
Report Number: NASA/TM-2000-210219
Report Number: NAS 1.15:210219
Meeting Information
Meeting: International Gas and Turbine and Aeroengine Technical Congress
Location: Munich
Country: Germany
Start Date: May 5, 2000
End Date: May 8, 2000
Sponsors: American Society of Mechanical Engineers
Funding Number(s)
PROJECT: RTOP 708-28-13
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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