The next generation aircraft combustor liner will be operating in more severe conditions. This means that the current cooling system needs significant amounts of cooling air to maintain cooling intensity. The present study investigates experimentally the total cooling effectiveness of an integrated impingement/effusion cooling system (thin perforated laminate plate) and effusion cooling system (single plate) at the same blowing ratio of 0.2 to 1.2. The infrared thermography method was employed to evaluate total cooling effectiveness and to determine the fully developed region of cooling performance. The holes arrays on both plates are 13 × 13 and the centers formed a square pattern (i.e., an in-line array). The perforated laminate plate is constructed of three layers and pins that were installed between the layers. In order to avoid increasing the thickness and volume, the layer thickness-to-hole diameter ratio was 0.29, and the pin height-to-hole diameter ratio, which is equivalent to the gap between the plates, was 0.21. The single plate had the same total plate thickness-to-hole diameter, but was composed of only one layer. As a result, the total cooling effectiveness of the laminate plate is 47% ∼ 141% better than single plate depending on the blowing ratio. Also, a fully developed region appears on the 2nd or 3th row of holes.
|Title of host publication||Heat Transfer|
|Publisher||American Society of Mechanical Engineers (ASME)|
|Publication status||Published - 2014|
|Event||ASME Turbo Expo 2014: Turbine Technical Conference and Exposition, GT 2014 - Dusseldorf, Germany|
Duration: 2014 Jun 16 → 2014 Jun 20
|Name||Proceedings of the ASME Turbo Expo|
|Other||ASME Turbo Expo 2014: Turbine Technical Conference and Exposition, GT 2014|
|Period||14/6/16 → 14/6/20|
Bibliographical notePublisher Copyright:
Copyright © 2014 by ASME.
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