大涵道比涡扇发动机循环参数和几何流路优化设计

Optimization of cycle parameters and gas path design for high bypass ratio turbofan engine

针对大涵道比涡扇发动机的特点,分析了涡扇发动机四个主要热力循环参数,即风扇外涵压比、总压比、涡轮前温度和涵道比及各循环参数的相互匹配关系对发动机单位推力和单位耗油率的影响。针对某大型飞机对巡航推力及巡航耗油率的要求,优化选择了满足涡扇发动机性能要求的四个主要热力循环参数,确定满足涡扇发动机性能的空气流量,并基于涡扇发动机的设计点参数对大涵道比涡扇发动机主要部件进行流路优化设计,最终确定涡扇发动机风扇直径,各主要部件进出口尺寸,最终得到整个涡扇发动机流路,获得满意的结果。

Effect of four main thermodynamic cycle parameters,fan pressure ratio,overall pressure ratio,turbine entry temperature,bypass ratio and the match of each parameter on engine specific thrust and specific fuel consumption were carried out for high bypass turbofan ratio engine.After the parametric study the four main thermodynamic parameters and mass flow which suit the desired curise thrust and specific fuel consumption for a civil aircraft were selected.Then,based upon these design point parameters the gas path of main components was designed for high bypass ratio turbofan engine.Finally the diameter of fan,and the dimension of fan,compressors and turbines were decided,and the result was ideal.