Research On Gas Distribution Design Method Of Combustor With Radial Swirler

The gas turbine had been widely used in many industrial fields of aviation,shipping,power,oil and so on as usual power equipment.Combustor is one of the three components of the gas turbine,and its performance directly affects fuel efficiency,turbine blade life,the overall efficiency of the gas turbine and gas turbine operating stability.With the development and progress of technology,the demands for gas turbine combustor are increasing in recent years.On one hand,the combustor wants to have lower emissions of gas and solid particles,longer life,more reasonable combustor exit temperature distribution,lower manufacturing and maintenance costs,on the other hand,requires a shorter design cycle to reduce costs and development risk of the gas turbine.According to this situation,this paper introduced a combustor design method,which is based on empirical method.This method can rapidly complete the flow distribution of the combustion chamber parts and the design of the structure,which is gained from empirical design method.Specific studies are as follows:(1)In this paper,the basic structural parameters of the gas turbine combustor were made from the empirical method;(2)The Chemkin software was used to build chemical reactor network and determine the proportion of ministries gas distribution.In this paper,the micro-element method was used to determine the effective reaction volume of each reaction zone in the combustion chamber and obtain the effective length of the combustion chamber;(3)Using Fluent software,this paper analysised two-dimensional model of the combustion chamber.The two-dimensional model was reasonably simplified and assumed.The optimal parameters of the two-dimensional model of structure were obtained;(4)Three-dimensional periodic expansion geometry is simulated to optimize the parameters of the three-dimensional geometry structure;(5)The paper analysied of three-dimensional model.The calculated combustion efficiency is 98.30%.The total pressure coefficient is 93.68%.The outlet temperature distribution factor is 17.68%.The outlet NO_x emission is 162.79ppm.Numerical results show that:the performance of the combustor,which is obtained from the design method,can meet the requirements.(6)This paper summarized and formed a complete gas turbine combustor design method.It provided some references for gas turbine combustor design.