Research on the Exit Temperature of a Heavy Duty Gas Turbine
A method of gas turbine overall performance evaluation was developed based on A 300 MW Class gas turbine,the effect of combustor exit OTDF&RTDF、turbine blade material and blade cooling mass flow are also added to this performance model.The accuracy of the method has been assessed by two different gas turbines,L20A and M701F3,where sufficient data can be reasonably derived from the open literature,the difference of gas turbine exit temperature are in 3℃.Some key parameters such as pressure ratio,compressor efficiency,combustor loss and temperature distribution,turbine stages,turbine efficiency,allowable metal temperature of turbine blade material and cooling mass flow were researched,and found that the effects of compressor pressure ratio,combustor temperature distribution,turbine stages and efficiency,blade material and cooling mass flow are quite big,and turbine stages have the biggest effect to gas turbine exit temperature.These parameters should be carefully considered in a new GT design to have the best GT exit temperature.
gas turbineoverall performance evaluationexit temperatureBrayton cycle
NETL
NSTL
万方数据
维普
