Aerodynamic Design And Analysis Of Gas Turbine For Heavy Duty Gas Turbines

The thermal efficiency of most advanced heavy gas turbine for single cycle and combined cycle have reached 40%~41% and 60%~61%,respectively.As the core power equipment for energy efficient conversion and clean use system,gas turbnes have become the most efficient large-scale commercial power generation in all thermal power conversion power generation systems.GE,SIEMENS,MITSUBISHI heavy industry major reburning companies have developed a more efficient and powerful H class or J grade heavy gas turbine to compete for the international market,and the development of our heavy gas turbine is in the pursuit stage.The aerodynamic design of the gas turbine,which is the core component of the gas turbine,is related to the performance of the whole turbine.Therefore,this paper has conducted the aerodynamic design of F and J turbines according to the design optimization system of the gas cooled turbine,and study the effect of the fourth stage guide vane bending on the last stage performance.First,one dimension design optimization,quasi three-dimensional design optimization and all 3D design and optimization adjustment are carried out on the 300 MW F class heavy gas cold turbine.The overall performance,the selectio n of the parameters,the three-dimensional flow field and the aerodynamic design characteristics of the multistage turbine provide a certain understanding.Finally,624 MW total power of the turbine,330 MW output power of the shaft end,593.35 kg/s turbine inlet flow,and 92.3% turbine efficiency are obtained to meet the design requirements.Secondly,the remolding idea of the 1600 C J reignition turbine is studied based on the F reignition turbine.It is necessary to adjust the work distribution,and finally make use of the advantages and characteristics of one dimensional design and quasi three-dimensional design,and complete the rapid adjustment of the work distribution.Finally,the dynamic design scheme of J grade reburning turbine gas is obtained.At last,the bending blade modeling for the last stage of the J turbine is studied,including the bending of the two ends and the bending of the top of the blade.Through the study,it is found that the design of the curved blade would affect the aerodynamic performance of the final guide vane and the moving blade,including the influence of the reactionary distribution and the strength of the shock structure.It is also found that the positive curved guide vane has a beneficial effect on the aerodynamic performance of the stage.