A study was undertaken to improve the prediction of external (gas-to-blade) heat transfer coefficients in gas turbine engines. The study specifically investigated the effects of improved modeling of the eddy diffusivity of heat in the turbulence model. A two- dimensional boundary layer code, STAN5, was selected and modified by incorporating several different turbulent Prandtl number models. Results indicated that slight effects were attributable to the modified turbulence model. Boundary layer character (laminar, turbulent or transitioning) appeared to be much more significant.
The Role of the Turbulent Prandtl Number in Turbine Blade Heat Transfer Prediction
Sae Technical Papers
Aerospace Technology Conference and Exposition ; 1990
1990-09-01
Conference paper
English
Turbine Blade Heat Transfer Prediction Using Coupled Turbulent Prandtl Number and Transition Models
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