Analysis to Reduce Emission Characteristics for Gas Turbine Combustion | Original Article
The main aim of this paper is a determine to reduce emission characteristic for gas turbine combustion. In semi empirical method of annular combustor design, there is a prediction for emission products (like nitrogen dioxide (NOx), carbon monoxide (CO), hydrocarbons (HC), smoke and residents) etc. To calculate the amount of emissions for flight operating conditions and landing takeoff condition where high radiation (NOx) occurred. In lean premix staged combustion, fuel and oxidizer (air) mixed before combustion at primary zone and it’s entirely different from diffusion flame combustion because combustion takes place simultaneously mixing of fuel and oxidizer (air). So lean premixed staged combustion process is the best way to reduce emission to minimize equivalence ratio of primary zone of annular combustor, so that its control the emission. In this method, we control emission through reduce specific fuel consumption (SFC) at landing and takeoff cycle (LTO cycle) and fuel-air ratio compare with stoichiometric equation of fuel and oxidizer (air). The engine thermodynamic state is mainly determined by the thrust demand of the aircraft, the ambient conditions and different flight missions have to be considered. Therefore a flight performance module is presented by using the technique of lean premix combustion to control the emission and to improve the performance of engine SFC.