某型涡扇发动机涡轮过渡流道一体化优化设计  

Integral Optimization Design for Intermediate Turbine Duct of Turbofan Engine

作　　者：侯朝山[1] 吴虎[1] 唐晓毅[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《计算机仿真》2013年第8期92-96,共5页Computer Simulation

摘　　要：研究大涵道比涡扇发动机涡轮过渡流道优化问题,针对扩张通道轴向长度较短,内部流动十分复杂,边界层气流容易分离等难点,为提高过渡流道气动性能,利用全三维数值仿真的方法对某型大涵道比涡扇发动机涡轮过渡流道进行了数值仿真,并采用遗传算法对初始流道进行了气动性能优化设计。仿真结果表明,过渡流道气动性能对其几何形状变化十分敏感,流量相同条件下,采用优化设计后,涡轮过渡流道压力系数提高,总压损失系数降低,并且流道稳定工作范围也得到改善,结果证明了优化方法的有效性和可行性。The short axial length,complex of inner flow and separation of boundary layer,make it hard to design the intermediate turbine duct of a high-bypass-ratio turbofan engine.To improve the aerodynamic performance,a numerical simulation was conducted by using three-dimensional numerical simulation on a certain type of diffuser.Later on,a genetic algorithm was adopted to optimize this original diffuser.It can be concluded from this optimization that the diffuser performance is highly sensitive to its geometry.Based on uniform mass flow,the static pressure coefficient has increased steeply,the total pressure loss coefficient has dropped,and even the stable operation range has been improved as well,which proved the effectiveness and feasibility of the optimization method.

关 键 词：涡轮过渡流道 优化设计 扩张通道 性能 稳定工作范围 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]