Combustor Wall Coolant Discharge Effects on Turbine Vane Endwall Curtain Cooling
Author:
Affiliation:
1. Xi’an Jiaotong University, 710049 Xi’an, People’s Republic of China
2. University of Minnesota, Minneapolis, Minnesota 55455
Funder
China Scholarship Council
National Natural Science Foundation of China
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
https://arc.aiaa.org/doi/pdf/10.2514/1.T5339
Reference25 articles.
1. Film Cooling of the Gas Turbine Endwall by Discrete-Hole Injection
2. Heat Transfer Committee Best Paper of 1995 Award: Distribution of Film-Cooling Effectiveness on a Turbine Endwall Measured Using the Ammonia and Diazo Technique
3. Adiabatic Effectiveness Measurements of Endwall Film-Cooling for a First-Stage Vane
4. Film-Cooled Turbine Endwall in a Transonic Flow Field: Part II—Heat Transfer and Film-Cooling Effectiveness
5. Design, Validation and Verification of Film Cooling on Gas Turbine Rotor Endwall
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1. Improving Turbine Endwall Overall Cooling Effectiveness Using Curtain Cooling and Redistributed Film-Hole Layouts: An Experimental and Computational Study;Journal of Thermal Science and Engineering Applications;2024-01-29
2. Recent Developments in the Aerodynamic Heat Transfer and Cooling Technology of Gas Turbines Endwalls;Aerospace;2023-08-09
3. TURBINE VANE ENDWALL FILM COOLING CONSIDERING FLOW NONUNIFORMITIES AND COOLANT INJECTION FROM UPSTREAM COMBUSTORS;Heat Transfer Research;2021
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