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Analytical and Experimental Evaluation of the Heat Transfer Distribution over the Surfaces of Turbine VanesThree airfoil data sets were selected for use in evaluating currently available analytical models for predicting airfoil surface heat transfer distributions in a 2-D flow field. Two additional airfoils, representative of highly loaded, low solidity airfoils currently being designed, were selected for cascade testing at simulated engine conditions. Some 2-D analytical methods were examined and a version of the STAN5 boundary layer code was chosen for modification. The final form of the method utilized a time dependent, transonic inviscid cascade code coupled to a modified version of the STAN5 boundary layer code featuring zero order turbulence modeling. The boundary layer code is structured to accommodate a full spectrum of empirical correlations addressing the coupled influences of pressure gradient, airfoil curvature, and free-stream turbulence on airfoil surface heat transfer distribution and boundary layer transitional behavior. Comparison of pedictions made with the model to the data base indicates a significant improvement in predictive capability.
Document ID
19830020105
Document Type
Contractor Report (CR)
Authors
Hylton, L. D.
(Detroit Diesel Allison Indianapolis, IN, United States)
Mihelc, M. S.
(Detroit Diesel Allison Indianapolis, IN, United States)
Turner, E. R.
(Detroit Diesel Allison Indianapolis, IN, United States)
Nealy, D. A.
(Detroit Diesel Allison Indianapolis, IN, United States)
York, R. E.
(Detroit Diesel Allison Indianapolis, IN, United States)
Date Acquired
September 4, 2013
Publication Date
May 1, 1983
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
NAS 1.26:168015
EDR-11209
NASA-CR-168015
Funding Number(s)
CONTRACT_GRANT: NAS3-22761
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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