INVESTIGATION OF THE EFFECT OF COLORLESS DISTRIBUTED COMBUSTION ON FLAME TEMPERATURE AND EMISSIONS IN A MINI GAS TURBINE ENGINE

Abstract

With the climate crisis, research has focused on emissions caused by fuels used for both civilian and military purposes. NOx emissions, which occur due to the high flame temperature in gas turbine combustion chambers used in aviation, are an important research topic. In this study, the colorless distributed combustion method, which has been observed to be beneficial in reducing NOx emissions in the literature, has been simulated by CFD in the combustion chamber of the mini turbojet engine. The outlet temperature of the combustion chamber of kerosene given from 12 jet nozzle by Discrete Phase Method (DPM) injection method with air at the rate of 21% O2 by volume under standard conditions was confirmed by the experimental data in the literature, with analyses made at different turbine rpm. After the validation study, the O2 ratio in the air was reduced to 19, 17, and 15%, respectively. According to the results obtained, the maximum temperature of the combustion chamber decreased from 2239 K to 1897 K, and NOx decreased from 16.3 PPM to 0.053 PPM.