Film-Cooling effectiveness of combined hole slot geometries on a turbine rotor blade surface
Author:
Funder
National Major Science and Technology Projects of China
Publisher
Elsevier BV
Reference44 articles.
1. Gas turbine film cooling;Bogard;J. Propul. Power,2006
2. A converging slot-hole film-cooling geometry—part 1: low-speed flat-plate heat transfer and loss;Sargison;J. Turbomach.,2002
3. A novel antivortex turbine film-cooling hole concept;Heidmann;J. Turbomach.,2008
4. Investigation on film cooling performance from a row of round-to-slot holes on flat plate;Zhang;Int. J. Therm. Sci.,2017
5. Comparative study on the adiabatic film cooling performances with elliptical or super-elliptical holes of various length-to-width ratios;Zhang;Int. J. Therm. Sci.,2020
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1. Experimental investigation on the effects of complex pressure gradients on the film cooling effectiveness of a serpentine nozzle;Applied Thermal Engineering;2024-10
2. Investigation on aerothermal characteristics of turbine blade tip clearance with large-scale and shrinkage groove;International Communications in Heat and Mass Transfer;2024-06
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