0
research-article

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

[+] Author and Article Information
Phillip Ligrani

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

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

Yin-hsiang 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:10.1115/1.4038248 History: Received July 25, 2017; Revised August 22, 2017

Abstract

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 18000, 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 degrees, 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 re-directed 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).

Copyright (c) 2017 by ASME
Your Session has timed out. Please sign back in to continue.

References

Figures

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In