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Research Papers

Combined Effects of Freestream Pressure Gradient and Density Ratio on the Film Cooling Effectiveness of Round and Shaped Holes on a Flat Plate

[+] Author and Article Information
Kyle R. Vinton, Travis B. Watson

Department of Mechanical Engineering,
Baylor University,
Waco, TX 76798-7356

Lesley M. Wright

Department of Mechanical Engineering,
Baylor University,
Waco, TX 76798-7356
e-mail: Lesley_Wright@Baylor.edu

Daniel C. Crites, Mark C. Morris, Ardeshir Riahi

Honeywell Aerospace,
Phoenix, AZ 85034

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received September 2, 2016; final manuscript received October 3, 2016; published online January 4, 2017. Editor: Kenneth Hall.

J. Turbomach 139(4), 041003 (Jan 04, 2017) (10 pages) Paper No: TURBO-16-1223; doi: 10.1115/1.4035044 History: Received September 02, 2016; Revised October 03, 2016

The combined effects of a favorable, mainstream pressure gradient and coolant-to-mainstream density ratio have been investigated. Detailed film cooling effectiveness distributions have been obtained on a flat plate with either cylindrical (θ = 30 deg) or laidback, fan-shaped holes (θ = 30 deg and β = γ = 10 deg) using the pressure-sensitive paint (PSP) technique. In a low-speed wind tunnel, both nonaccelerating and accelerating flows were considered, while the density ratio varied from 1 to 4. In addition, the effect of blowing ratio was considered, with this ratio varying from 0.5 to 1.5. The film produced by the shaped hole outperformed the round hole under the presence of a favorable pressure gradient for all the blowing and density ratios. At the lowest blowing ratio, in the absence of freestream acceleration, the round holes outperformed the shaped holes. However, as the blowing ratio increases, the shaped holes prevent lift-off of the coolant and offer enhanced protection. The effectiveness afforded by both the cylindrical and shaped holes, with and without freestream acceleration, increased with density ratio.

Copyright © 2017 by ASME
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References

Figures

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Fig. 1

Low-speed wind tunnel for film cooling investigations

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Fig. 2

Validation of FPG insert

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Fig. 3

Details of film hole configurations

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Fig. 4

PSP calibration curve

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Fig. 5

Film cooling effectiveness distributions for round holes under zero-pressure gradient

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Fig. 6

Film cooling effectiveness distributions for shaped holes under zero-pressure gradient

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Fig. 7

Laterally averaged film cooling effectiveness for round holes with zero-pressure gradient

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Fig. 8

Laterally averaged film cooling effectiveness for shaped holes with zero-pressure gradient

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Fig. 9

Film cooling effectiveness distributions for round holes under favorable pressure gradient

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Fig. 10

Film cooling effectiveness distributions for shaped holes under favorable pressure gradient

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Fig. 11

Laterally averaged film cooling effectiveness for round holes with a favorable pressure gradient

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Fig. 12

Laterally averaged film cooling effectiveness for shaped holes with a favorable pressure gradient

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Fig. 13

Overall surface-averaged film cooling effectiveness for round holes varied with momentum flux ratio (I)

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Fig. 14

Overall surface-averaged film cooling effectiveness for shaped holes varied with momentum flux ratio (I)

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Fig. 15

Validation of current experimental investigation

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Fig. 16

Overall surface average film cooling effectiveness for zero-pressure gradient varied with momentum flux ratio (I)

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Fig. 17

Overall surface average film cooling effectiveness for favorable pressure gradient varied with momentum flux ratio (I)

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