Investigation of Thermal Effect on Bypass Transition on a High-Pressure Turbine Guide Vane
Author:
Affiliation:
1. Jacques Chauvin Laboratory, Turbomachinery and Propulsion Department, von Karman Institute for Fluid Dynamics, Rhode-Saint-Genèse B1640, Belgium e-mail:
Abstract
Publisher
ASME International
Subject
Mechanical Engineering
Link
http://asmedigitalcollection.asme.org/turbomachinery/article-pdf/doi/10.1115/1.4041909/6311390/turbo_141_05_051006.pdf
Reference33 articles.
1. The Role of Laminar-Turbulent Transition in Gas Turbine Engines;ASME J. Turbomach.,1991
2. The Laminar-Turbulent Transition in a Boundary-Layer—Part I;J. Aeronaut. Sci.,1951
3. Di Pasquale, D., Rona, A., and Garrett, S. J., 2009, “A Selective Review of Transition Modelling for CFD,” AIAA Paper No. AIAA 2009-3812https://www2.le.ac.uk/departments/engineering/people/academic-staff/sjg50/2009-3812.pdf.
4. Nonadiabatic Surface Effects on Transition Measurements Using Temperature-Sensitive Paints;AIAA J.,2015
5. An Experimental Convective Heat Transfer Investigation Around a Film-Cooled Gas Turbine Blade;ASME J. Turbomach.,1990
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