TY - GEN
T1 - Variation in Convective and Radiative Heat Transfer with Reynolds Number and Temperature in a Backward-Facing Step Combustor
AU - Colborn, Jennifer
AU - O’Connor, Jacqueline
N1 - Publisher Copyright:
© 2023, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2023
Y1 - 2023
N2 - Flow fields in gas turbine combustors have a wide variety of flow features near the combustor liner, including recirculation, shear layer separation and impingement, and boundary-layer development. As a result, modeling and predicting the heat transfer to the liner is challenging. The current work seeks to investigate the relative contributions of convective and radiative heat transfer to combustor liners using a backward-facing step combustor. Backward-facing step flows have many features relevant to gas turbines in a two-dimensional geometry, allowing for simpler modeling and easier instrumentation. Reynolds number, air temperature, and temperature of the combustor floor were varied to determine the impact of each parameter on the heat transfer through the different combustor zones: the recirculation, impingement, and recovery zones. Using a heat flux sensor and a radiometer, the total and radiative heat flux in these different zones was measured, respectively. Total heat flux was much higher than radiative heat flux, indicating the importance of convection heat transfer at these conditions. Increases in air and plate temperature increased both total and radiative heat transfer. Additionally, the highest heat flux was observed in the impingement zone and the lowest heat transfer was usually observed in the recirculation zone.
AB - Flow fields in gas turbine combustors have a wide variety of flow features near the combustor liner, including recirculation, shear layer separation and impingement, and boundary-layer development. As a result, modeling and predicting the heat transfer to the liner is challenging. The current work seeks to investigate the relative contributions of convective and radiative heat transfer to combustor liners using a backward-facing step combustor. Backward-facing step flows have many features relevant to gas turbines in a two-dimensional geometry, allowing for simpler modeling and easier instrumentation. Reynolds number, air temperature, and temperature of the combustor floor were varied to determine the impact of each parameter on the heat transfer through the different combustor zones: the recirculation, impingement, and recovery zones. Using a heat flux sensor and a radiometer, the total and radiative heat flux in these different zones was measured, respectively. Total heat flux was much higher than radiative heat flux, indicating the importance of convection heat transfer at these conditions. Increases in air and plate temperature increased both total and radiative heat transfer. Additionally, the highest heat flux was observed in the impingement zone and the lowest heat transfer was usually observed in the recirculation zone.
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U2 - 10.2514/6.2023-0923
DO - 10.2514/6.2023-0923
M3 - Conference contribution
AN - SCOPUS:85194042578
SN - 9781624106996
T3 - AIAA SciTech Forum and Exposition, 2023
BT - AIAA SciTech Forum and Exposition, 2023
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA SciTech Forum and Exposition, 2023
Y2 - 23 January 2023 through 27 January 2023
ER -