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Open Access

Heat transfer characteristics in a narrow confined channel with discrete impingement cooling

Yang LIaTao LIUaJianjun TAOaWeihua YANGb( )Likun DONGa
Hunan Key Laboratory of Turbomachinery on Small and Medium Aero-Engine, AECC Hunan Aviation Powerplant Research Institute, Zhuzhou 412002, China
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Peer review under responsibility of Editorial Committee of CJA.

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Abstract

Heat transfer characteristics in a narrow confined channel with discrete impingement cooling were investigated using thermal infrared camera. Detailed heat transfer distributions and comparisons on three surfaces with three impact diameters were experimentally studied in the range of Reynolds number of 3000 to 30000. The experimental results indicated that the strong impingement jet leaded to a high strength heat transfer zone in the ΔX=±2.5Dj range of the impact center, which was 1.3–2.5 times of the average heat transfer value of the impingement wall. With the same coolant mass flow rate, small diameter case had lower heat transfer coefficient on both inner wall and outside wall, while the impingement wall was insensitive to the impact diameter. The surface averaged Nusselt number of inner wall was only 43%–57% of impingement wall, while the outside wall can reach up to 80%–90%. The larger the diameter, the higher heat transfer enhancement and the smaller the channel flow resistance was observed in term of Reynolds number. The surface averaged Nusselt numbers were developed as the function of Reynolds number and the impingement height-to-diameter for further engineering applications.

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Chinese Journal of Aeronautics
Pages 220-229

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Cite this article:
LI Y, LIU T, TAO J, et al. Heat transfer characteristics in a narrow confined channel with discrete impingement cooling. Chinese Journal of Aeronautics, 2022, 35(4): 220-229. https://doi.org/10.1016/j.cja.2021.08.022

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Received: 14 December 2020
Revised: 05 January 2021
Accepted: 13 April 2021
Published: 21 October 2021
© 2021 Chinese Society of Aeronautics and Astronautics.

This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/).