Benchmarking of Computational Models Against Experimental Data for Adiabatic Film-Cooling Effectiveness for Large Spacing Compound Angle Full Coverage Film Cooling Arrays
Date of Award
Thesis - Open Access
Master of Science in Aerospace Engineering
Dr. Mark Ricklick
First Committee Member
Dr. Magdy Attia
Second Committee Member
Dr. Sandra Boetcher
This study aims to benchmark experimental data that tested the effects of blowing ratio, surface angle, and hole spacing for two full coverage geometries composed of cylindrical staggered holes at a compound angle of 45 degrees. These holes varied parametrically the inclination angle to be 30 and 45 degrees, while maintaining a lateral and axial spacing of 14.5 hole diameters. Within this study, the local film cooling effectiveness was obtained from 30 rows for the 14.5 diameter spacing. Utilizing a velocity profile at the crossflow inlet produced significant differences in the results produced when compared to a uniform freestream velocity profile. The goal of this research is to use commercially available turbulence models, in an effort to provide a benchmarking effect that matches the trusted experimental data found in past experiments. From this study, out of the 7 turbulence model cases tested, it was found that the k - ω Shear Stress Transport turbulence model with no curvature correction provided the best representation of the experimental results being benchmarked.
Scholarly Commons Citation
Martinez, Simon R., "Benchmarking of Computational Models Against Experimental Data for Adiabatic Film-Cooling Effectiveness for Large Spacing Compound Angle Full Coverage Film Cooling Arrays" (2015). Doctoral Dissertations and Master's Theses. 226.