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Research Papers: Jets, Wakes, and Impingment Cooling

On the Flow Structures and Adiabatic Film Effectiveness for Simple and Compound Angle Hole With Varied Length-to-Diameter Ratio by Large Eddy Simulation and Pressure-Sensitive Paint Techniques

[+] Author and Article Information
Weihong Li

Gas Turbine Institute,
Department of Thermal Engineering,
Tsinghua University,
Beijing 100084, China
e-mail: Liwh13@mails.tsinghua.edu.cn

Wei Shi

Gas Turbine Institute,
Department of Thermal Engineering,
Tsinghua University,
Beijing 100084, China
e-mail: shiwei15@mails.tsinghua.edu.cn

Xueying Li

Gas Turbine Institute,
Department of Thermal Engineering,
Tsinghua University,
Beijing 100084, China
e-mail: lixueying@mail.tsinghua.edu.cn

Jing Ren

Gas Turbine Institute,
Department of Thermal Engineering,
Tsinghua University,
Beijing 100084, China
e-mail: renj@tsinghua.edu.cn

Hongde Jiang

Gas Turbine Institute,
Department of Thermal Engineering,
Tsinghua University,
Beijing 100084, China

1Corresponding author.

Contributed by the Heat Transfer Division of ASME for publication in the JOURNAL OF HEAT TRANSFER. Manuscript received October 12, 2016; final manuscript received May 24, 2017; published online August 9, 2017. Assoc. Editor: Danesh K. Tafti.

J. Heat Transfer 139(12), 122201 (Aug 09, 2017) (13 pages) Paper No: HT-16-1653; doi: 10.1115/1.4037085 History: Received October 12, 2016; Revised May 24, 2017

The effects of hole length-to-diameter ratio and compound angle on flat plate film cooling effectiveness are investigated from an experimental and numerical view. Film cooling effectiveness measurements are performed for seven blowing ratios (M) ranging from 0.3 to 2, five-hole length-to-diameter ratios (L/D) from 0.5 to 5, and two compound angles (β: 0 deg and 45 deg) using pressure-sensitive paint (PSP) technique. Results indicate that discrete holes with L = 0.5 and 1 show highest film cooling effectiveness regardless of compound angle. Round hole generally shows an increasing trend as L increases from 2 to 5, while compound angle hole shows a complex trend concerning with blowing ratios (BRs) and length-to-diameter ratios. Compound angle enhances film cooling effectiveness with high blowing ratios and length-to-diameter ratios. In a parallel effort, large eddy simulation (LES) approach is employed to solve the flow field and visualize vortex structures of intube and mainstream regions. It is demonstrated that the counter-rotating vortex pair (CRVP) which is observed in the time-averaged flow field is originated in different vortex structures with varying blowing ratios and length-to-diameter ratios. Scalar field transportation features are also investigated to clarify how different vortex structures affect the temperature distribution and the film cooling effectiveness.

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Figures

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Fig. 1

Schematic view of the low-speed wind tunnel

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Fig. 2

Approach boundary layers measured at x/D = −10 for film cooling measurements

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Fig. 3

Film hole configurations: (a) simple angle hole and (b) compound angle hole

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Fig. 4

PSP calibration curves under different temperature conditions

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Fig. 5

Spanwise-averaged film cooling effectiveness comparison with published data: (a) simple angle hole and (b) compound angle hole

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Fig. 6

Film cooling effectiveness distribution for (a) simple angle hole and (b) compound angle hole at M = 0.8 with varied length-to-diameter ratio

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Fig. 7

Spanwise-averaged film cooling effectiveness with varied length-to-diameter ratio and blowing ratio: (a) simple angle hole, M = 0.5, (b) compound hole, M = 0.5, (c) simple angle hole, M = 1.5, and (d) compound hole, M = 1.5

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Fig. 8

Film cooling effectiveness distribution for simple angle hole and compound angle hole with (a) L/D = 0.5 and (b) L/D = 3.5 with varied blowing ratio

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Fig. 9

Computational domain with mainflow and coolant

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Fig. 10

Mean velocity comparison with experimental data by Pietrzyk et al. [30]

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Fig. 11

Fluctuation velocity comparison with experimental data by Pietrzyk et al. [30]

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Fig. 12

Film cooling effectiveness contour comparison of simple angle hole for three blowing ratios with L/D = 5

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Fig. 13

Film cooling effectiveness contour comparison of simple angle hole for three blowing ratios with L/D = 0.5

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Fig. 14

Plane positions for L/D = 2 and L/D = 5

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Fig. 15

Intube nondimensional axis velocity Un/Uj comparison of simple angle hole for M = 0.8: (a) L/D = 2, (b) L/D = 5, (c) LES of Bodart et al. [31], and (d) experimental data of Bodart et al. [31]

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Fig. 16

Intube nondimensional axis vorticity ωnD/Uj comparison of simple angle hole for M = 0.8: (a) L/D = 2 and (b) L/D = 5

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Fig. 17

Instantaneous vortical structures and time-averaged ωx vorticity distribution for simple angle hole with L/D = 2: (a) instantaneous results and (b) time-averaged results

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Fig. 18

Instantaneous vortical structures and time-averaged ωx vorticity distribution for simple angle hole with M = 0.8: (a) instantaneous results and (b) time-averaged results

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Fig. 19

Time-averaged Q value isosurface and ωx vorticity distribution for simple angle hole with M = 0.4 and varied length-to-diameter ratio: (a) L/D = 0.5, (b) L/D = 2, and (c) L/D = 5

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Fig. 20

Time-averaged dimensionless temperature distributions at three planes and film effectiveness distributions for simple angle hole with varied L/D, M = 0.8

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Fig. 21

Film cooling effectiveness comparison between experimental and LES results for compound angle hole with M = 0.8

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Fig. 22

Time-averaged streamwise vorticity ωx distribution and crossflow streamlines of compound angle hole: (a) L/D = 2 and (b) L/D = 5, M = 0.8

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