Experimental investigation and optimization of fuel injector in gas turbine engine in trinary region

Abstract

Conversion of bulk liquid in to small droplets raging in sub microns to several hundred of microns that process is Atomization it is a complicated process. Fuel injection is a necessary component for all high pressure engine because the air must precisely controlled due to extreme pressure and temperature found in high compression turbine engine on the trinary range This kind of simplex injector finds its use in combustor (Direct injection method The need to minimize the combustor length usually leads to a spray angle of around more than 60 o . The experimental investigations of simplex plain jet injector for spray cone angle and penetrant length at
different injection pressure ranging from 0.5bar to 3bar in an increment of 0.5bar is carried out. The results are then compared with different injector dimensions of 2mm, and 2.5mm with water and Keresan as fuel. The discharge coefficient and the spray cone angle were evaluated experimentally and compared with the available data. The investigation and optimization of fuel injection is carried out to identify the different spraying stages so that combustion can be sustained and mixing of air –fuel is time lined. Furthermore the
mixing enhances the combustion followed by increase in combustion efficiency and low emission