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research-article

DOUBLE WALL COOLING OF A FULL COVERAGE EFFUSION PLATE WITH CROSS FLOW SUPPLY COOLING AND MAIN FLOW PRESSURE GRADIENT

[+] Author and Article Information
Phillip Ligrani

Propulsion Research Center, Department of Mechanical and Aerospace Engineering, 5000 Technology Drive, Olin B. King Technology Hall S236, University of Alabama in Huntsville, Huntsville, Alabama 35899 USA
pml0006@uah.edu

Zhong Ren

Propulsion Research Center, Department of Mechanical and Aerospace Engineering, 5000 Technology Drive, Olin B. King Technology Hall S236, University of Alabama in Huntsville, Huntsville, Alabama 35899 USA
zr0003@uah.edu

Sneha Vanga

Propulsion Research Center, Department of Mechanical and Aerospace Engineering, 5000 Technology Drive, Olin B. King Technology Hall S236, University of Alabama in Huntsville, Huntsville, Alabama 35899 USA
sv0025@uah.edu

Christopher Allgaier

ITLR University of Stuttgart, Pfaffenwaldring 31, 70569 Stuttgart, Germany
christopher.allgaier@alice.de

Federico Liberatore

Combustion Engineering, Solar Turbines, Inc., 2200 Pacific Highway, Mail Zone E-4, San Diego, California 92186-5376 USA
Liberatore_Fred_X@solarturbines.com

Rajeshriben Patel

Combustion Engineering, Solar Turbines, Inc., 2200 Pacific Highway, Mail Zone E-4, San Diego, California 92186-5376 USA
Patel_Rajeshriben@solarturbines.com

Ram Srinivasan

Combustion Engineering, Solar Turbines, Inc., 2200 Pacific Highway, Mail Zone E-4, San Diego, California 92186-5376 USA
srinivasan_ram@solarturbines.com

Shaun Ho

Combustion Engineering, Solar Turbines, Inc., 2200 Pacific Highway, Mail Zone E-4, San Diego, California 92186-5376 USA
Ho_Shaun@solarturbines.com

1Corresponding author.

ASME doi:10.1115/1.4041451 History: Received July 30, 2018; Revised August 20, 2018

Abstract

Experimentally measured results are presented for a test plate with double wall cooling, comprised of full-coverage effusion-cooling on the hot-side of the plate, and cross-flow cooling on the cold-side of the plate. The results presented include the effects of a mainstream pressure gradient. With this arrangement, local blowing ratio decreases significantly with streamwise development along the test section, for every value of initial blowing ratio considered, where this initial value is determined at the most upstream row of effusion holes. Experimental data are given for a sparse effusion hole array. The experimental results are provided for mainstream Reynolds numbers of 92400 to 96600, and from 128400 to 135000, and initial blowing ratios of 3.3-3.6, 4.4, 5.2, 6.1-6.3, and 7.3-7.4. Results illustrate the effects of blowing ratio for the hot-side and the cold-side of the effusion plate. Of particular interest are values of line-averaged film cooling effectiveness and line-averaged heat transfer coefficient, which are generally different for contraction ratio of 4, compared to a contraction ratio of 1, because of different amounts and concentrations of effusion coolant near the test surface. In regard to cold-side measurements on the crossflow side of the effusion plate, line-averaged Nusselt numbers for contraction ratio 4 are often less than values for contraction ratio 1, when compared at the same main flow Reynolds number, initial blowing ratio, and streamwise location.

Solar Turbines Incorporated
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