TY - GEN
T1 - Wall-Resolved LES Study of Shaped-Hole Film Cooling Flow for Varying Hole Orientation
AU - Nunno, A. Cody
AU - Wu, Sicong
AU - Ameen, Mushin M.
AU - Pal, Pinaki
AU - Kundu, Prithwish
AU - Abouhussein, Ahmed
AU - Peet, Yulia T.
AU - Joly, Michael M.
AU - Cocks, Peter A.
N1 - Funding Information:
The submitted manuscript has been created by UChicago Argonne, LLC, Operator of Argonne National Laboratory (Argonne). Argonne, a U.S. Department of Energy Office of Science laboratory, is operated under Contract No. DEAC02-06CH11357. The U.S. Government retains for itself, and others acting on its behalf, a paid-up nonexclusive, irrevocable worldwide license in said article to reproduce, prepare derivative works, distribute copies to the public, and perform publicly and display publicly, by or on behalf of the Government. The research work was funded by the DOE Advanced Manufacturing Office (AMO) through the High Performance Computing for Energy Innovation (HPC4EI) program. The authors thank Dr. Robert Shroeder from Sargent and Lundy and Prof. Karen Thole from Pennsylvania State University for sharing the CAD file of the 7-7-7 shaped hole configuration. Lastly, the authors would like to acknowledge the computing core hours available through the Bebop cluster provided by the Laboratory Computing Resource Center (LCRC) at Argonne National Laboratory and National Energy Research Scientific Computing Center (NERSC) Cori supercomputer for this research.
Publisher Copyright:
© 2022, American Institute of Aeronautics and Astronautics Inc.. All rights reserved.
PY - 2022
Y1 - 2022
N2 - This work presents the findings from a wall-resolved large-eddy simulation (WRLES) study of a canonical gas turbine film cooling configuration performed using a high-order spectral element computational fluid dynamics (CFD) solver known as Nek5000. In particular, flow over a flat plate with a single row of 7-7-7 shaped cooling holes (represented by a single hole with periodic boundary conditions in the spanwise direction) was examined. Numerical results for the baseline case comprised of blowing ratio (BR) of 2, density ratio of 1.6, inlet freestream Reynolds number of 6000, and 30° cooling hole orientation relative to the mean flow were compared with available experimental data. Thereafter, simulations for hole angles of 25°, 35°, and 40° were performed (at BR = 2) to analyze the impact of hole orientation on the adiabatic cooling effectiveness profiles; blowing ratio was also varied (keeping the cooling hole angle fixed at 30°) to investigate its impact on adiabatic effectiveness. With respect to cooling hole angle, it was found that the 30° case had the best peak cooling effectiveness, whereas the 25° case exhibited a broader effectiveness profile with a lower peak due to the plenum flow being more aligned with the bulk flow. On the other hand, lower blowing ratio cases showed a wider film cooling effectiveness profile, but lower overall cooling effectiveness downstream of the cooling hole due to the specifics of the chosen configuration.
AB - This work presents the findings from a wall-resolved large-eddy simulation (WRLES) study of a canonical gas turbine film cooling configuration performed using a high-order spectral element computational fluid dynamics (CFD) solver known as Nek5000. In particular, flow over a flat plate with a single row of 7-7-7 shaped cooling holes (represented by a single hole with periodic boundary conditions in the spanwise direction) was examined. Numerical results for the baseline case comprised of blowing ratio (BR) of 2, density ratio of 1.6, inlet freestream Reynolds number of 6000, and 30° cooling hole orientation relative to the mean flow were compared with available experimental data. Thereafter, simulations for hole angles of 25°, 35°, and 40° were performed (at BR = 2) to analyze the impact of hole orientation on the adiabatic cooling effectiveness profiles; blowing ratio was also varied (keeping the cooling hole angle fixed at 30°) to investigate its impact on adiabatic effectiveness. With respect to cooling hole angle, it was found that the 30° case had the best peak cooling effectiveness, whereas the 25° case exhibited a broader effectiveness profile with a lower peak due to the plenum flow being more aligned with the bulk flow. On the other hand, lower blowing ratio cases showed a wider film cooling effectiveness profile, but lower overall cooling effectiveness downstream of the cooling hole due to the specifics of the chosen configuration.
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U2 - 10.2514/6.2022-1404
DO - 10.2514/6.2022-1404
M3 - Conference contribution
AN - SCOPUS:85123589945
SN - 9781624106316
T3 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022
BT - AIAA SciTech Forum 2022
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022
Y2 - 3 January 2022 through 7 January 2022
ER -