Effect of Film-Hole Shape on Turbine-Blade Heat-Transfer Coefficient Distribution
Author:
Affiliation:
1. Texas A&M University, College Station, Texas 77843-3123
2. NASA John H. Glenn Research Center at Lewis Field, Cleveland, Ohio 44135-3191
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Condensed Matter Physics,Aerospace Engineering,Space and Planetary Science,Fluid Flow and Transfer Processes,Mechanical Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/2.6610
Reference24 articles.
1. An Experimental Study of Turbine Vane Heat Transfer With Leading Edge and Downstream Film Cooling
2. Heat Transfer and Film Cooling Effectiveness in a Linear Airfoil Cascade
3. Investigation of Detailed Film Cooling Effectiveness and Heat Transfer Distributions on a Gas Turbine Airfoil
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