Benchmarking of Computational Models Against Experimental Data for Adiabatic Film-Cooling Effectiveness for Large Spacing Compound Angle Full Coverage Film Cooling Arrays

<p>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.</p>

Name thesis:degree_name

Master of Science in Aerospace Engineering

Level thesis:degree_level

Thesis - Open Access

Discipline thesis:degree_discipline

Aerospace Engineering

Year

2015

Author dc:creator

• Martinez, Simon R.

• benchmarking
• adiabatic
• film cooling
• Aerospace Engineering

Repository record dc:identifier

https://commons.erau.edu/edt/226

OAI identifier oai:identifier

oai:commons.erau.edu:edt-1225