Impingement cooling of gas turbine components (original) (raw)
1984, High Temperature Technology
Impingement cooling heat transfer data were obtained for test geometries relevant to full coverage gas turbine combustion chamber wall cooling with the full flame tube pressure loss across the impingement plate. An impingement hole pitch to diameter ratio (X/D) of between 10 and 13 is appropriate for this application and two test geometries within this range were studied. The impingement gap to hole diameter ratio (Z/D) was the main parameter studied together with the hole Reynolds number. A significant influence of Z/D on the heat transfer was found and a general correlation equation derived. Evidence of enhanced impingement heat transfer for Z/D less than unity was found.
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