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Research Papers: Jets, Wakes, and Impingment Cooling

# The Effect of Weak Crossflow on the Heat Transfer Characteristics of Short-Distance Impinging Cooling

[+] Author and Article Information
Chuanjie Zhang

National Key Laboratory of Science
and Technology on Aero-Engine
Aero-Thermodynamics,
Beihang University,
Haidian District,
Beijing 100191, China
e-mail: Zhangcj0123@163.com

Guoqiang Xu

National Key Laboratory of Science
and Technology on Aero-Engine
Aero-Thermodynamics,
Beihang University,
Haidian District,
Beijing 100191, China
e-mail: guoqiang_xu@buaa.edu.cn

Haiwang Li

National Key Laboratory of Science
and Technology on Aero-Engine
Aero-Thermodynamics,
Beihang University,
Haidian District,
Beijing 100191, China
e-mail: 19820912@sina.com

Jining Sun

National Key Laboratory of Science
and Technology on Aero-Engine
Aero-Thermodynamics,
School of Energy and Power Engineering,
Beihang University,
Haidian District,
Beijing 100191, China
e-mail: Sunjining@buaa.edu.cn

Na Cai

Qingdao Branch,
Qingdao 266041, China
e-mail: caina0532@126.com

1Corresponding author.

Contributed by the Heat Transfer Division of ASME for publication in the JOURNAL OF HEAT TRANSFER. Manuscript received October 17, 2013; final manuscript received July 14, 2014; published online August 18, 2014. Assoc. Editor: Danesh / D. K. Tafti.

J. Heat Transfer 136(11), 112201 (Aug 18, 2014) (11 pages) Paper No: HT-13-1542; doi: 10.1115/1.4028081 History: Received October 17, 2013; Revised July 14, 2014

## Abstract

This paper numerically and experimentally investigated the effect of weak crossflow on the heat transfer characteristics of a short-distance impinging jet. The Reynolds number of the impinging jet ranged from 6000 to 15,000, and the mass velocity ratio (M) between the crossflow and the jet varied from 0 to 0.15. The separation distance (H) between the exit of the jet nozzle and the impingement surface equals to the exit diameter (D) of the impinging jet. In the experiments, the temperature distribution on the impingement target surface was measured using a transient liquid crystal method. In the numerical simulation, a multiblock hexahedral mesh was applied to discrete the computational domain, and a commercial CFD package (Ansys cfx-12.0) with a standard $k-ɛ$ turbulence model was used for computation. It was found that compared to the impinging cooling without crossflow, the heat transfer characteristics near the impinging stagnation point remained almost constant. At the same time, the presence of crossflow decreased the heat transfer rate in the upstream region of the impinging stagnation point, while increased that in the downstream of the impinging stagnation point. Taken together, crossflow has a complex influence on the impinging cooling, which is highly dependent on the mass velocity ratio between the crossflow and the jet.

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## Figures

Fig. 4

The Hue value and temperature value calibration curve

Fig. 3

Experimental model ((a) lateral view and (b) top view)

Fig. 2

Experimental apparatus

Fig. 1

Combined cooling of the impingement and film

Fig. 6

Experiment result of spanwise average mixing Nusselt number distribution along streamline at different ratios mass velocity ratios (a) Rej = 10,000 and (b) Rej = 12,000

Fig. 7

Numerical computing model

Fig. 5

Experimental result of mixing Nusselt number distribution on the impingement surface (a) Rej = 10,000 and (b) Rej = 12,000

Fig. 9

Comparison of calculation results for the standard k-ɛ model with different grids

Fig. 10

Typical grid of numerical computing model

Fig. 13

Spanwise average adiabatic Nusselt number distribution along streamline at different mass velocity ratios

Fig. 14

Difference between spanwise average adiabatic Nusselt number with and without crossflow along streamline at different mass velocity ratios

Fig. 11

Computation result of spanwise average mixing Nusselt number distribution along streamline at different ratios mass velocity ratios (a) Rej = 10,000 and (b) Rej = 12,000

Fig. 12

Velocity vector diagram of impinging center section (a) M = 0, (b) M = 0.08, and (c) M = 0.12

Fig. 18

Velocity contours close to the wall (a) M = 0, (b) M = 0.08, and (c) M = 0.12

Fig. 19

Typical flow around a cylinder [28]

Fig. 8

Comparison between calculation results of different turbulence models and experimental results (a) Rej = 10,000 M = 0 and (b) Rej = 10,000 M = 0.12

Fig. 15

Adiabatic Nusselt number distribution at impingement surface (a) M = 0, (b) M = 0.08, and (c) M = 0.12

Fig. 16

Pressure contours on central section of impingement hole (a) M = 0, (b) M = 0.08, and (c) M = 0.12

Fig. 17

Velocity contours on central section of impingement hole (a) M = 0, (b) M = 0.08, and (c) M = 0.12

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