Swirl Impinging Cooling on an Airfoil Leading Edge Model at Large Reynolds Number

[+] Author and Article Information
Nian Wang

Turbine Heat Transfer Laboratory, Department of Mechanical Engineering, Texas A&M University, College Station, TX, USA

Dr. Je-Chin Han

Turbine Heat Transfer Laboratory, Department of Mechanical Engineering, Texas A&M University, College Station, TX, USA

1Corresponding author.

ASME doi:10.1115/1.4042151 History: Received November 07, 2017; Revised November 30, 2018


Jet impingement cooling has been extensively investigated due to its significant applications on the airfoil leading edge region, however, most of which are about normal jet impingement. The systematic research on swirl jet impinging cooling on leading edge is relatively rare. The present study comprehensively investigated the heat transfer distribution of swirl jet impingement with one row of tangential jets. The location of the cross-over jets is offset from the centerline toward either suction or pressure side. Five jet Reynolds numbers varying from 10,000 to 80,000 are tested to reach real engine cooling condition. Jet plates with jet-to-jet spacing (s/d = 2, 4 and 6) and the ratio of surface diameter-to-jet diameter (D/d = 4, 6.6 and 13.3) are tested. We conducted the experiments with a test matrix of 45 cases. The optimum geometric parameters of the jet plate are revealed. Results indicate that for a given Reynolds number the jet plate configuration with D/d = 4 and s/d = 2 provides the highest Nusselt number profile than the other jet plate configurations, while the jet plate configuration with D/d = 13.3 and s/d = 8 provides the lowest Nusselt number profiles. The best heat transfer region shifts by varying the jet plate configuration depending on the strength of swirl flow. Additionally, correlation of tangential jet impingement has been developed to predict the area-averaged Nusselt number, which is useful for airfoil leading edge cooling design and heat transfer analysis.

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