Effect of Slot Area Ratio and Slot Angle on Swirl Cooling in a Gas Turbine Blade Leading Edge
Publication: Journal of Aerospace Engineering
Volume 33, Issue 5
Abstract
This paper numerically simulated a swirl cooling system to study the influences of the slot area ratio and slot angle on the flow field and heat transfer performance. Numerical simulations were performed for different coolant inlet to outlet slot area ratios (1, 2, 3, and 4) and slot angles (60°, 75°, 90°, and 105°) at different Reynolds numbers. Results indicate that large-scale vortices and small circular or oval vortices are generated in the cooling channel at different slot area ratios and slot angles. At identical Reynolds numbers, the cooling system achieved 30% and 23% increases in global Nusselt number and thermal performance factor, respectively, when the slot area ratio increased from 1 to 4. Although the system obtained only a 7.5% increase in global Nusselt number, it achieved a 29.8% increase in thermal performance factor when the slot angle increased from 60° to 105° at fixed Reynolds number. The applied cooling system is recommended for the internal swirl cooling of a gas turbine blade leading edge at optimum values of design parameters at a slot area ratio of 4 and slot angle 105° at high Reynolds number.
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Data Availability Statement
All data, models, and code generated or used during the study appear in the published article.
Acknowledgments
The authors are grateful for the support of the National Natural Science Foundation of China (Nos. 51809065 and 51741901), and the Ph.D. Student Research and Innovation Fund of the Fundamental Research Funds for the Central Universities (Grant No. 3072019GIP0304).
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©2020 American Society of Civil Engineers.
History
Received: Sep 21, 2019
Accepted: Mar 3, 2020
Published online: May 21, 2020
Published in print: Sep 1, 2020
Discussion open until: Oct 21, 2020
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