大涵道比涡扇发动机涡轮过渡段的数值研究  

Numerical Research for Intermediate Turbine Duct of High Bypass Turbo-fan Engine

作　　者：毛凯[1] 吴虎[1] 徐倩楠[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《科学技术与工程》2012年第6期1308-1313,共6页Science Technology and Engineering

摘　　要：采用CFD数值模拟方法对大涵道比涡扇发动机高压涡轮与低压涡轮之间的过渡流道进行了气动性能计算。通过与实验数据的对比,验证了CFD计算模型预测涡轮过渡段气动性能的可靠性以及计算精度。分析了径向偏移较大的涡轮过渡段流动特点和损失机理,为进一步提高过渡段气动性能提供研究方向。高性能大涵道比发动机中,涡轮过渡流道流动机理复杂,设计难度大,其可供挖掘潜力较大。The aerodynamic performance calculation of high-pressure turbine and low-pressure turbine intermediate duct were numerically simulated. With experimental data, the dependability and accuracy of CFD calculation model for predicting the performance of turbine intermediate duct had been verified. The flow characteristics and the loss mechanism had been analyzed in turbine intermediate duct with large radial offset, in order to provide research direction for improving the aerodynamic performance of ITD further. The improving design of intermediate duct is meaningful to the high bypass turbofan engine.

关 键 词：大涵道比涡扇发动机 涡轮过渡流道 数值模拟 损失 

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]