Computational Conjugate Heat Transfer Analysis of HP Stage Turbine Blade Cooling: Effect of Turbulator Geometry in Helicoidal Cooling Duct
In a bid to improve turbine entry temperature for maximizing the thermal efficiency of the HP stage gas turbine blade, an attempt is made in this paper to compare the performance of helicoidal ducted blade cooling with turbulator of different geometric proportion. It is found from analysis that there is significant improvement in cooling characteristics for turbine blade with turbulator geometry having larger e/D ratio. Also it is found from analysis, performance is vastly improved for greater thickness of turbulator geometry.
Digital Object Identifier (DOI): doi.org/10.5281/zenodo.1075154Procedia APA BibTeX Chicago EndNote Harvard JSON MLA RIS XML ISO 690 PDF
 Chandrakant R Kini, Satish Shenoy B, and N Yagnesh Sharma (2012), "Numerical Analysis of Gas Turbine HP Stage Blade Cooling with New Cooling Duct Geometries", International Journal of Earth Sciences and Engineering, Volume 05 No 04 (02), pp. 1057-1062.
 Chandrakant R Kini, Satish Shenoy B, and N Yagnesh Sharma (2012), "Numerical Analysis of Gas Turbine HP Stage Blade Cooling with New Cooling Duct Geometries", 2nd International Engineering Symposium - IES 2012, Kumamoto University, Japan, March 5-7.
 Chandrakant R Kini, Satish Shenoy B, and N Yagnesh Sharma (2011), "A Computational Conjugate Thermal Analysis of HP Stage Turbine Blade Cooling with Innovative Cooling Passage Geometries", The 2011 International Conference of Mechanical Engineering, World Congress of Engineers, London, July 6-8.
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