Experimental investigation of effusion and film cooling for gas turbine combustor

Inanli, S.; Yasa, T.; Ulas, A.

dc.contributor.author	Inanli, S.	en
dc.contributor.author	Yasa, T.	en
dc.contributor.author	Ulas, A.	en
dc.date.accessioned	2017-08-28T07:08:42Z
dc.date.available	2017-08-28T07:08:42Z
dc.date.issued	2016	en
dc.description	Papers presented to the 12th International Conference on Heat Transfer, Fluid Mechanics and Thermodynamics, Costa de Sol, Spain on 11-13 July 2016.	en
dc.description.abstract	Experimental study was conducted to understand the heat transfer characteristics of film or effusion cooled test plates that represent the gas turbine combustor liner. Two effusion cooling test plates having different hole angles (30 and 75° with horizontal) were used. Film cooling tests were conducted by six different slot geometries. Test geometries were the scaled-up model of real combustor liner. Three different blowing ratios were applied for each test plate geometry. Surface cooling effectiveness was determined for each test condition by measuring the surface temperature distribution by infrared thermography technique. Effects of geometrical and flow parameters on cooling effectiveness were investigated.
dc.format.extent	6 pages	en
dc.format.medium	PDF	en
dc.identifier.uri	http://hdl.handle.net/2263/62098
dc.language.iso	en	en
dc.publisher	HEFAT	en
dc.rights	University of Pretoria	en
dc.subject	Effusion and film cooling	en
dc.subject	Gas turbine combustor	en
dc.title	Experimental investigation of effusion and film cooling for gas turbine combustor	en
dc.type	Presentation	en