Date of Award
6-2007
Document Type
Thesis
Degree Name
Master of Science in Aeronautical Engineering
Department
Department of Aeronautics and Astronautics
First Advisor
Mark F. Reeder, PhD
Abstract
An effort was undertaken to understand the impact of different film cooling configurations in a true scale turbine vane for three proprietary airfoil designs. The measurements for this study were taken at the United States Air Force Turbine Research Facility (TRF). The TRF enabled heat transfer data to be obtained on full scale turbine hardware under realistic engine conditions. The surface heat flux of the turbine blades was analyzed using the impulse response method. The overall effectiveness was compared between airfoil types at 60% span over varying streamwise locations on both suction and pressure surfaces. Using an approximated massflow, a comparison of the overall effectiveness with respect to massflow rate could be made between airfoils at three different airfoil locations. The shaped hole and slot cooling configurations were found to have higher average overall effectiveness for lower massflow rates than the multiple hole configuration based on the conditions tested.
AFIT Designator
AFIT-GAE-ENY-07-J21
DTIC Accession Number
ADA470649
Recommended Citation
Umholtz, Michael J., "A Comparison of Film Cooling Techniques in a High Speed, True Scale, Fully Cooled Turbine Vane Ring" (2007). Theses and Dissertations. 2952.
https://scholar.afit.edu/etd/2952