Computational investigation of film cooling from cylindrical and row trenched cooling holes near the combustor endwall
Author:
Publisher
Elsevier BV
Subject
Fluid Flow and Transfer Processes,Engineering (miscellaneous)
Reference23 articles.
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3. Flow field computations of combustor–turbine interactions relevant to a gas turbine engine;Stitzel;J Turbomach,2004
4. Experimental study of the effect of dilution jets on film cooling flow in a gas turbine combustor [Ph.D. thesis];Scrittore,2008
5. Kianpour E, Sidik NAC, Agha Seyyed Mirza Bozorg M. Thermodynamicanalysis of flow field atthe end of combustor simulator. In: Proceedings of the AEROTECH IV conference, Kuala Lumpur, Malaysia; 2012, AMM.225.261.
Cited by 2 articles. 订阅此论文施引文献 订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献
1. A Detailed Study of Row-Trenched Holes at the Combustor Exit on Film-Cooling Effectiveness;Mechanics and Mechanical Engineering;2019-06-01
2. A DETAILED STUDY OF EFFECTS OF ROW TRENCHED HOLES AT THE COMBUSTOR EXIT ON FILM COOLING EFFECTIVENESS;Journal of the Serbian Society for Computational Mechanics;2017-12
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