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Research Papers: Gas Turbines: Heat Transfer

Nonuniform Jet Array Impingement on a Curved Surface

[+] Author and Article Information
Jahed Hossain

Laboratory for Turbine Aerodynamics,
Heat Transfer and Durability,
Center for Advanced Turbomachinery
and Energy Research,
University of Central Florida,
12781 Ara Drive,
Orlando, FL 32826
e-mail: Jahed.hossain@knights.ucf.edu

John Harrington

Laboratory for Turbine Aerodynamics, Heat
Transfer and Durability,
Center for Advanced Turbomachinery
and Energy Research,
University of Central Florida,
12781 Ara Drive,
Orlando, FL 32826
e-mail: John.harrington@knights.ucf.edu

Wenping Wang

Laboratory for Turbine Aerodynamics,
Heat Transfer and Durability,
Center for Advanced Turbomachinery
and Energy Research,
University of Central Florida,
12781 Ara Drive,
Orlando, FL 32826
e-mail: Wenping.wang@ucf.edu

Jayanta Kapat

Laboratory for Turbine Aerodynamics,
Heat Transfer and Durability,
Center for Advanced Turbomachinery
and Energy Research,
University of Central Florida,
12781 Ara Drive,
Orlando, FL 32826
e-mail: Jayanta.kapat@ucf.edu

Steven Thorpe

Ansaldo Energia Switzerland,
Romerstrasse 36,
Baden 5401, Switzerland
e-mail: steven.thorpe@ansaldoenergia.com

Michael Maurer

Ansaldo Energia Switzerland,
Romerstrasse 36,
Baden 5401, Switzerland
e-mail: Michaelthomas.maurer@ansaldoenergia.com

Contributed by the Heat Transfer Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received May 20, 2017; final manuscript received June 14, 2017; published online December 19, 2017. Editor: David Wisler.

J. Eng. Gas Turbines Power 140(5), 051902 (Dec 19, 2017) (10 pages) Paper No: GTP-17-1174; doi: 10.1115/1.4038023 History: Received May 20, 2017; Revised June 14, 2017

Experiments to investigate the effect of varying jet hole diameter and jet spacing on heat transfer and pressure loss from jet array impingement on a curved target surface are reported. The jet plate configurations studied have varying hole diameters and geometric spacing for spatial tuning of the heat transfer behavior. The configuration also includes a straight section downstream of the curved section, where the effect on heat transfer and pressure loss is also investigated. The jet plate holes are sharp-edged. A steady-state measurement technique utilizing temperature-sensitive paint (TSP) was used on the target surface to obtain local heat transfer coefficients. Pressure taps placed on the sidewall and jet plate of the channel were used to evaluate the flow distribution in the impingement channel. For all configurations, spent air is drawn out in a single direction which is tangential to the target plate curvature. First row jet Reynolds numbers ranging from 50,000 to 160,000 are reported. Further tests were performed to evaluate several modifications to the impingement array. These involve blocking several downstream rows of jets, measuring the subsequent shifts in the pressure and heat transfer data, and then applying different turbulator designs in an attempt to recover the loss in the heat transfer while retaining favorable pressure loss. It was found that by using W-shaped turbulators, the downstream surface average Nusselt number increases up to ∼13% as compared with a smooth case using the same amount of coolant. The results suggest that by properly combining impingement and turbulators (in the post impingement section), higher heat transfer, lower flow rate, and lower pressure drop are simultaneously obtained, thus providing an optimal scenario.

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References

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Harrington, J. , Hossain, J. , Wang, W. , Kapat, J. , Maurer, M. , and Thorpe, S. , 2017, “ Effect of Target Wall Curvature on Heat Transfer and Pressure Loss From Jet Array Impingement,” ASME J. Turbomach., 139(5), p. 051004. [CrossRef]
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Figures

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Fig. 1

Test section cross-sectional view

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Fig. 2

CAD model of jet plate for all the cases (the heated area is shown in red color)

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Fig. 8

Laterally averaged Nusselt number comparison for case3

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Fig. 9

Target surface Nusselt number contours for cases 1–3 at Rej,1 = 125,000

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Fig. 10

Laterally averaged Nusselt number comparison of cases 1–3

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Fig. 7

Target surface Nusselt number contours for case 3

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Fig. 6

Pressure drop inside the channel

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Fig. 5

Experimental jet Reynolds number distribution for case 3

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Fig. 4

Experimental local jet-to-row 1 jet mass flux ratio for cases 1–3

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Fig. 3

Experimental local jet-to-row 1 jet mass flux ratio for cases 1–3

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Fig. 11

Downstream Nusselt number profiles for cases 1–5 at Rej,1 = 125,000

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Fig. 12

Nusselt number at downstream straight section for cases 2–5 at Rej,1 = 125,000

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Fig. 13

Rib Pitch-averaged Nusselt number for cases 2, 4, and, 5 at Rej,1 = 125,000

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