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http://dx.doi.org/10.5293/kfma.2016.19.4.013

Comparative Study on the Film Cooling Effectiveness of 15° Angled Anti-Vortex Hole and 30-7-7 Fan-Shaped Hole Using PSP Technique  

Kim, Ye Jee (School of Aerospace and Mechanical Engineering, Korea Aerospace University)
Park, Soon Sang (School of Aerospace and Mechanical Engineering, Korea Aerospace University)
Rhee, Dong Ho (Korea Aerospace Research Institute)
Kwak, Jae Su (School of Aerospace and Mechanical Engineering, Korea Aerospace University)
Publication Information
The KSFM Journal of Fluid Machinery / v.19, no.4, 2016 , pp. 13-18 More about this Journal
Abstract
The various film cooling hole shapes have been proposed for effective external cooling of gas turbine blade. In this study, the film cooling effectiveness by three different hole shapes (cylindrical hole, $15^{\circ}$ angle anti-vortex hole, 30-7-7 fan-shaped hole) were examined experimentally. Pressure Sensitive Paint (PSP) technique was used to measure the film cooling effectiveness. The coolant to mainstream density ratio was 1.0 and three blowing ratios of 0.5, 1.0, and 2.0 were considered. Results clearly showed that the effect of hole shape on the distribution of film cooling effectiveness. For the cylindrical hole case, the film cooling effectiveness decreased remarkably as the blowing ratio increased due to the jet lift off. Because of large hole exit area and low coolant momentum, the 30-7-7 fan-shaped hole case showed the highest film cooling effectiveness at all blowing ratio, followed by the anti-vortex hole case.
Keywords
Film Cooling; Film Cooling Effectiveness; Gas Turbine; Pressure Sensitive Paint;
Citations & Related Records
Times Cited By KSCI : 3  (Citation Analysis)
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