One And Three Dimensional Design Methodology Of Low Emission Gas Turbine Combustor

Currently gas turbine technology is widely used,which produces a more obvious pollutant.Controlling its pollutant emissions has become many scholars’ subject of extensive research worldwide,and for the time-consuming process and other issues in gas turbine combustor design,this paper presents one-dimensional design and three-dimensional verification methodology of gas turbine combustor in target low emission,which can provide some useful guidance for combustor design.In this paper,one-dimensional design is achieved by the application of CHEMKIN-PRO software.Firstly,based on the flow field organization status of gas turbine combustor,liner space is splitted to different zones,building correspondent chemical reactor network model,then by adjusting the ratio of the head of the regional air intake we can achieve a best value of air distribution ratio,where the outlet of the gas turbine combustor has the lowest NOx emission.And then using the micro-element method characterized by the reaction zone status effective volume content of each partition will be got.The results show that the swirler intake ratio,the head intake ratio of the combustion zone and the intermediate main combustion zone intake ratio were 19.5%,5.5% and 25%,which can keep the lowest levels of NOx emissions at the outlet of the combustor,and three-dimensional geometry can provide sufficient reaction space.One-dimensional optimal flow distribution is applied to three-dimensional numerical verification,and based on the description of the combustor through the establishment of the flow field the basic equations and additional state equation,using FLUENT software examines the impact of the swirler structure and characteristics of injection on the combustion performance,getting the optimal flow field and performance status.The results show that the combustion efficiency is increased with an increase in vane numbers,vane angle and vane thickness.Both at a smaller distance between swirler and primary holes and a lower flow channel width,there is an increase in combustion efficiency.However the pattern factor of exit temperature distribution has the opposite change.The total pressure recovery coefficient is increased with a decrease in vane numbers,vane angle and vane thickness,and an increase in flow channel width.The combustion efficiency is improved with both lower nozzledistance and spray cone angle.The pattern factor of exit temperature distribution is reduced with a decrease in nozzle distance and an increase in spray cone angle.The total pressure recovery coefficient is increased with a increase in nozzle distance,a reduce in spray cone angle and a increase in mean spray oil diameter,and the spray oil velocity has no effect on the total pressure recovery coefficient.Finally by the new CRN model combining detailed chemical reaction mechanism an accurate prediction emission is achieved,furthermore,the air temperature and fuel injection temperature at the entrance of the combustor for emissions affecting situation are examined.And the NOx emission is 50.7ppm,which increases exponentially along with the combustor inlet air temperature but increases linearly with the fuel spray temperature.