Total-coverage discrete hole wall cooling

Hyung Hee Cho, Richard J. Goldstein

Research output: Chapter in Book/Report/Conference proceedingConference contribution

1 Citation (Scopus)


The present study investigates heat/mass transfer for flow through perforated plates for application to combustor wall and turbine blade film cooling. The experiments are conducted for hole length-to-diameter ratios of 0.68 to 1.5, for hole pitch-to-diameter ratios of 1.5 and 3.0, for gap distance between two parallel perforated plates of 0 to 3 hole diameters, and for Reynolds numbers of 60 to 13,700. Local heat/mass transfer coefficients near and inside the cooling holes are obtained using a naphthalene sublimation technique. Detailed knowledge of the local transfer coefficients is essential to analyze thermal stress in turbine components. The results indicate that the heat/mass transfer coefficients inside the hole surface vary significantly due to flow separation and reattachment. The transfer coefficient near the reattachment point is about four and half times that for a fully developed circular tube flow. The heat/mass transfer coefficient on the leeward surface has the same order as that on the windward surface because of a strong recirculation flow between neighboring jets from the array of holes. For flow through two in-line layers, the transfer coefficient affected by the gap spacing is approximately 100% higher on the windward surface of the second wall and is about 20% lower on the inside hole surface than that with a single layer. The transfer coefficient on the leeward surface is not affected by upstream flow conditions due to probably strong recirculation in the wake flow.

Original languageEnglish
Title of host publicationHeat Transfer; Electric Power; Industrial and Cogeneration
PublisherAmerican Society of Mechanical Engineers (ASME)
ISBN (Electronic)9780791878811
Publication statusPublished - 1995
EventASME 1995 International Gas Turbine and Aeroengine Congress and Exposition, GT 1995 - Houston, United States
Duration: 1995 Jun 51995 Jun 8

Publication series

NameProceedings of the ASME Turbo Expo


OtherASME 1995 International Gas Turbine and Aeroengine Congress and Exposition, GT 1995
Country/TerritoryUnited States

Bibliographical note

Funding Information:
Support from the Air Force Office of Scientific Research and through the Engineering Research Program of the Department of Energy aided greatly in the conduct of this study.

Publisher Copyright:
Copyright © 1995 by ASME All Rights Reserved.

All Science Journal Classification (ASJC) codes

  • Engineering(all)


Dive into the research topics of 'Total-coverage discrete hole wall cooling'. Together they form a unique fingerprint.

Cite this