Experimental investigation on the combined cooling methods of jet impingement and film cooling for the pressure surface of the turbine vane leading cavity
Author:
Funder
National Major Science and Technology Projects of China
Publisher
Elsevier BV
Reference38 articles.
1. Review of gas turbine internal cooling improvement technology;Nourin;J. Energy Resour. Technol.,2021
2. A review of recent studies on rotating internal cooling for gas turbine blades;Yeranee;Chin. J. Aeronaut.,2021
3. Impingement/film cooling of C3X vane with double-wall cooling structure using air/mist mixture;Zhang;Int. J. Heat. Mass Transf.,2022
4. Effect of mass flow ratios on the conjugate heat transfer of a metal turbine vane at medium temperature;Cheng;Int. J. Heat. Mass Transf.,2023
5. Film Cooling;Goldstein,1971
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1. Heat transfer in rotating impingement channels with asymmetric curvature target surfaces for different channel orientations and jet hole shapes;International Communications in Heat and Mass Transfer;2024-09
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