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Research Papers: Gas Turbines: Heat Transfer

Double Wall Cooling of a Full-Coverage Effusion Plate, Including Internal Impingement Array Cooling

[+] Author and Article Information
Phil Ligrani

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

Zhong Ren

Department of Mechanical and
Aerospace Engineering,
Propulsion Research Center,
University of Alabama in Huntsville,
5000 Technology Drive, Olin B. King
Technology Hall,
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 Heat Transfer Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received July 25, 2017; final manuscript received August 22, 2017; published online December 6, 2017. Assoc. Editor: Riccardo Da Soghe.

J. Eng. Gas Turbines Power 140(5), 051901 (Dec 06, 2017) (9 pages) Paper No: GTP-17-1393; doi: 10.1115/1.4038248 History: Received July 25, 2017; Revised August 22, 2017

New experimental data are provided for full-coverage effusion cooling and impingement array cooling, as applied simultaneously onto the respective external and internal surfaces of a single instrumented test plate. For the effusion cooled surface, presented are spatially resolved distributions of surface adiabatic film cooling effectiveness, and surface heat transfer coefficients. For the impingement cooled surface, presented are spatially resolved distributions of surface Nusselt numbers. Impingement jet arrays at different jet Reynolds numbers, from 7930 to 18,000, are employed. Experimental data are given for spanwise and streamwise impingement hole spacing such that coolant jet hole centerlines are located midway between individual effusion hole entrances. For the effusion cooling, streamwise hole spacing and spanwise hole spacing (normalized by effusion hole diameter) are 15 and 4, respectively. Effusion hole angle is 25 deg, and effusion plate thickness is 3.0 effusion hole diameters. In regard to the impingement cooled cold-side surface of the effusion plate, associated surface Nusselt number variations provide evidence that impingement jets are turned and redirected as they cross the impingement passage, just prior to the entrance of coolant into individual effusion holes. In regard to the effusion cooled hot-side surface of the effusion plate, when compared at particular values of injectant and mainstream Reynolds numbers, streamwise location x/de and blowing ratio BR, significantly increased thermal protection is provided when the effusion coolant is provided by an array of impingement cooling jets (compared to a cross flow channel supply arrangement).

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References

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Figures

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Fig. 1

Side, cross-sectional view of the test section, including optical instrumentation arrangements, from Rogers et al. [12]

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Fig. 2

Impingement plate, from Rogers et al. [12]

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Fig. 3

Relative positions of impingement holes and effusion holes, from Rogers et al. [12]

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Fig. 4

Comparisons of normalized pressure drop variations for different effusion jet Reynolds numbers for ReMS = 142,000–155,000

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Fig. 5

Comparison of local, spatially resolved surface Nusselt number variations for different blowing ratios for ReMS = 142,000–155,000: (a) BR = 3.3, (b) BR = 4.3, (c) BR = 5.5, (d) BR = 6.3, and (e) BR = 7.4

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Fig. 6

Comparison of line-averaged surface Nusselt numbers with streamwise development for different blowing ratios for ReMS = 142,000–155,000. Solid rectangles denote effusion hole entrance streamwise locations. Dashed rectangles denote impingement hole streamwise locations.

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Fig. 7

Comparison of spatially averaged surface Nusselt numbers with streamwise development for different blowing ratios for ReMS = 142,000–155,000

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Fig. 8

Surface, local heat transfer coefficient variation for BR = 7.4 and ReMS = 142,000

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Fig. 9

Surface, local adiabatic film cooling effectiveness variation for BR = 6.3 and ReMS = 146,000

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Fig. 10

Comparisons of line-averaged heat transfer coefficient values with streamwise development for different blowing ratios for ReMS = 142,000–155,000

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Fig. 11

Comparisons of line-averaged adiabatic film cooling effectiveness with streamwise development for different blowing ratios for ReMS = 142,000–155,000: (a) effectiveness based upon stagnation cross flow conditions and (b) effectiveness based upon stagnation impingement plenum conditions

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Fig. 12

Comparisons of line-averaged heat transfer coefficient values with streamwise development for different mainstream Reynolds number values of ReMS = 99,000–109,000 and ReMS = 142,000–155,000: (a) BR = 4.3 and (b) BR = 6.3–6.4

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Fig. 13

Comparisons of line-averaged adiabatic film cooling effectiveness with streamwise development for different mainstream Reynolds number values of ReMS = 99,000–109,000 and ReMS = 142,000–155,000: (a) BR = 4.3 and (b) BR = 6.3–6.4

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Fig. 14

Comparisons of line-averaged heat transfer coefficient values with streamwise development for impingement flow coolant supply and cross flow coolant supply: (a) BR = 4.3 and (b) BR = 6.3

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Fig. 15

Comparisons of line-averaged adiabatic film cooling effectiveness with streamwise development for impingement flow coolant supply and cross flow coolant supply: (a) BR = 4.3 and (b) BR = 6.3

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