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Research Papers

Double Wall Cooling of a Full-Coverage Effusion Plate With Main Flow Pressure Gradient, Including Internal Impingement Array Cooling

[+] Author and Article Information
Sneha Reddy Vanga, David Ritchie, Austin Click, Zhong Ren

Department of Mechanical and
Aerospace Engineering,
Propulsion Research Center,
5000 Technology Drive,
Olin B. King Technology Hall S236,
University of Alabama in Huntsville,
Huntsville, AL 35899

Phil Ligrani

Professor
Department of Mechanical and
Aerospace Engineering,
Propulsion Research Center,
5000 Technology Drive,
Olin B. King Technology Hall University of
Alabama in Huntsville,
Huntsville, AL 35899
e-mail: pml0006@uah.edu

Federico Liberatore, Rajeshriben Patel, Ram Srinivasan, Yin-Hsiang Ho

Combustion Engineering,
Solar Turbines, Inc.,
2200 Pacific Highway, Mail Zone E-4,
San Diego, CA 92186-5376

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received August 14, 2018; final manuscript received October 11, 2018; published online January 21, 2019. Editor: Kenneth Hall.

J. Turbomach 141(4), 041002 (Jan 21, 2019) (11 pages) Paper No: TURBO-18-1200; doi: 10.1115/1.4041750 History: Received August 14, 2018; Revised October 11, 2018

The present study provides new effusion cooling data for both the surfaces of the full-coverage effusion cooling plate. For the effusion-cooled surface, presented are spatially resolved distributions of surface adiabatic film cooling effectiveness and surface heat transfer coefficients (measured using transient techniques and infrared thermography). For the impingement-cooled surface, presented are spatially resolved distributions of surface Nusselt numbers (measured using steady-state liquid crystal thermography). To produce this cool-side augmentation, impingement jet arrays at different jet Reynolds numbers, from 2720 to 11,100, are employed. Experimental data are given for a sparse effusion hole array, with spanwise and streamwise impingement hole spacing such that coolant jet hole centerlines are located midway between individual effusion hole entrances. Considered are the initial effusion blowing ratios from 3.3 to 7.5, with subsonic, incompressible flow. The velocity of the freestream flow which is adjacent to the effusion-cooled boundary layer is increasing with streamwise distance, due to a favorable streamwise pressure gradient. Such variations are provided by a main flow passage contraction ratio CR of 4. Of particular interest are effects of impingement jet Reynolds number, effusion blowing ratio, and streamwise development. Also, included are comparisons of impingement jet array cooling results with: (i) results associated with crossflow supply cooling with CR = 1 and CR = 4 and (ii) results associated with impingement supply cooling with CR = 1, when the mainstream pressure gradient is near zero. Overall, the present results show that, for the same main flow Reynolds number, approximate initial blowing ratio, and streamwise location, significantly increased thermal protection is generally provided when the effusion coolant is provided by an array of impingement cooling jets, compared to a crossflow coolant supply.

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References

Andrews, G. E. , Asere, A. A. , Husain, C. I. , Mkpadi, M. C. , and Nazari, A. , 1988, “ Impingement/Effusion Cooling: Overall Wall Heat Transfer,” ASME Paper No. 88-GT-290.
Al Dabagh, A. M. , Andrews, G. E. , Abdul Husain, R. A. A. , Husain, C. I. , Nazari, A. , and Wu, J. , 1990, “ Impingement/Effusion Cooling: The Influence of the Number of Impingement Holes and Pressure Loss on the Heat Transfer Coefficient,” ASME J. Turbomach., 112(3), pp. 467–476. [CrossRef]
Andrews, G. E. , Al-Dabagh, A. M. , Asere, A. A. , Bazdidi-Tehrani, F. , Mkpadi, M. C. , and Nazari, A. , 1992, “ Impingement/Effusion Cooling,” AGARD Conference 527, 80th Symposium on Heat Transfer and Cooling in Gas Turbines, AGARD Propulsion and Energetics Panel, Antalya, Turkey, Oct. 12–16, pp. 30.1–30.10.
Andrews, G. E. , and Nazari, A. , 1999, “ Impingement/Effusion Cooling: Influence of Number of Holes On the Cooling Effectiveness For An Impingement X/D of 10.5 and Effusion X/D of 7.0,” GTSJ International Gas Turbine Congress, Vol. II, Paper No. IGTC TS-51.
Cho, H. H. , and Rhee, D. H. , 2001, “ Local Heat/Mass Transfer Measurement on the Effusion Plate in Impingement/Effusion Cooling Systems,” ASME J. Turbomach., 123(3), pp. 601–608. [CrossRef]
Hong, S. K. , Rhee, D. H. , and Cho, H. H. , 2007, “ Effects of Fin Shapes and Arrangements on Heat Transfer for Impingement/Effusion Cooling With Cross-Flow,” ASME J. Heat Transfer, 129(12), pp. 1697–1707. [CrossRef]
Cho, H. H. , Rhee, D. H. , and Goldstein, R. J. , 2008, “ Effects of Hole Arrangements on Local Heat/Mass Transfer for Impingement/Effusion Cooling With Small Hole Spacing,” ASME J. Turbomach., 130(4), p. 041003.
Miller, M. , Natsui, G. , Ricklick, M. , Kapat, J. , and Schilp, R. , 2014, “ Heat Transfer in a Coupled Impingement-Effusion Cooling System,” ASME Paper No. GT2014-26416.
Shi, B. , Li, J. , Li, M. , Ren, J. , and Jiang, H. , 2016, “ Cooling Effectiveness on a Flat Plate With Both Film Cooling and Impingement Cooling in Hot Gas Conditions,” ASME Paper No. GT2016-57224.
El-Jummah, A. M. , Andrews, G. E. , and Staggs, J. E. J. , 2016, “ Impingement/Effusion Cooling Wall Heat Transfer Conjugate Heat Transfer Computational Fluid Dynamic Predictions,” ASME Paper No. GT2016-56961.
El-Jummah, A. M. , Nazari, A. , Andrews, G. E. , and Staggs, J. E. J. , 2017, “ Impingement/Effusion Cooling Wall Heat Transfer: Reduced Number of Impingement Jet Holes Relative to the Effusion Holes,” ASME Paper No. GT2017-63494.
Oguntade, H. I. , Andrews, G. E. , Burns, A. D. , Ingham, D. B. , and Pourkashanian, M. , 2017, “ Impingement/Effusion Cooling With Low Coolant Mass Flow,” ASME Paper No. GT2017-63484.
Rogers, N. , Ren, Z. , Buzzard, W. , Sweeney, B. , Tinker, N. , Ligrani, P. M. , Hollingsworth, K. D. , Liberatore, F. , Patel, R. , Ho, S. , and Moon, H.-K. , 2016, “ Effects of Double Wall Cooling Configuration and Conditions on Performance of Full Coverage Effusion Cooling,” ASME Paper No. GT2016-56515.
Ligrani, P. , Ren, Z. , Liberatore, F. , Patel, R. , Srinivasan, R. , and Ho, Y. , 2017, “ Double Wall Cooling of a Full-Coverage Effusion Plate, Including Internal Impingement Array Cooling,” ASME Paper No. IMECE2017-72066.
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Figures

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Fig. 1

Test section configuration. (a) side, cross-sectional view of the test section, including optical instrumentation arrangements, from Rogers et al. [1] and (b) side and top views of effusion plate, including normalized streamwise coordinate systems.

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Fig. 2

Comparisons of main stream static gage pressure with CR = 1 and CR = 4 impingement flow data and CR = 4 crossflow data for Rems = 103,000–110,000 and Rems,avg = 147,000 –160,000

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Fig. 3

Comparisons of local blowing ratio with CR = 1 impingement flow data and CR = 4 impingement flow data for Rems = 103,000–110,000 and Rems,avg = 147,000–160,000

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Fig. 4

Comparisons of cold-side local, spatially resolved surface Nusselt number variations for different blowing ratios for Rems = 148,000–152,000 and Rems,avg = 211,000–219,000: (a) BR = 3.3, (b) BR = 4.5, (c) BR = 5.3, (d) BR = 6.2, and (e) BR = 7.0

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Fig. 5

Comparisons of cold-side line-averaged surface Nusselt numbers with streamwise development for different blowing ratios for Rems = 148,000–152,000 and Rems,avg = 211,000 –219,000. Solid rectangles denote effusion hole entrance streamwise locations. Dashed rectangles denote impingement hole streamwise locations.

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Fig. 6

Comparisons of cold-side spatially averaged surface Nusselt numbers with streamwise development for different blowing ratios for Rems = 148,000–152,000 and Rems,avg = 211,000–219,000

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Fig. 7

Comparisons of cold-side line-averaged Nusselt number with streamwise development for an impingement flow coolant supply: (a) BR = 4.5, CR = 4, and BR = 4.3, CR = 1 and (b) BR = 5.3, CR = 4, and BR = 5.5, CR = 1

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Fig. 8

Comparisons of cold-side line-averaged Nusselt number with streamwise development for an impingement flow coolant supply and a crossflow coolant supply: (a) BR = 4.5, CR = 4, and BR = 4.3, CR = 4 and (b) BR = 5.3, CR = 4, and BR = 5.5, CR = 4

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Fig. 9

Hot-side surface, local heat transfer coefficient variation for BR = 6.6, Rems = 104,000, and Rems,avg = 150,000

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Fig. 10

Hot-side surface, local adiabatic film cooling effectiveness variation for BR = 7.5, Rems = 104,000, and Rems,avg = 147,000

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Fig. 11

Comparisons of hot-side line-averaged heat transfer coefficient values with streamwise development for different blowing ratios for Rems = 103,000–110,000 and Rems,avg = 147,000–160,000

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Fig. 12

Comparisons of hot-side line-averaged adiabatic film cooling effectiveness with streamwise development for different blowing ratios for Rems = 103,000–110,000 and Rems,avg = 147,000–160,000

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Fig. 13

Comparisons of hot-side line-averaged heat transfer coefficient values with streamwise development for an impingement flow coolant supply with CR = 4 and a crossflow coolant supply with CR = 1: (a) BR = 5.1 and BR = 5.5 and (b) BR = 6.4 and BR = 6.6

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Fig. 14

Comparisons of hot-side line-averaged adiabatic film cooling effectiveness values with streamwise development for an impingement flow coolant supply with CR = 4 and a crossflow coolant supply with CR = 1: (a) BR = 5.1 and BR = 5.5 and (b) BR = 6.4 and BR = 6.6

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Fig. 15

Comparisons of hot-side line-averaged heat transfer coefficient values with streamwise development for an impingement flow coolant supply with CR = 1 and CR = 4: (a) BR = 5.1 and BR = 5.5 and (b) BR = 7.4 and BR = 7.5

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Fig. 16

Comparisons of hot-side line-averaged adiabatic film cooling effectiveness values with streamwise development for an impingement flow coolant supply with CR = 1 and CR = 4: (a) BR = 5.1 and BR = 5.5 and (b) BR = 7.4 and BR = 7.5

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Fig. 17

Comparisons of hot-side line-averaged heat transfer coefficient values with streamwise development for an impingement flow coolant supply with CR = 4 and a crossflow coolant supply with CR = 4: (a) BR = 5.1 and BR = 5.2 and (b) BR = 6.6 and BR = 6.1

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Fig. 18

Comparisons of hot-side line-averaged adiabatic film cooling effectiveness values with streamwise development for an impingement flow coolant supply with CR = 4 and a crossflow coolant supply with CR = 4: (a) BR = 5.1 and BR = 5.2 and (b) BR = 6.6 and BR = 6.1

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