大涵道比发动机多级低压涡轮气动设计

基于大涵道比航空发动机多级低压涡轮设计研究,分析了大涵道比发动机多级低压涡轮气动设计特点和主要设计参数的设计选取原则以及发展趋势,研究了过渡流道设计参数的选取标准、过渡流道优化设计方法以及对多级低压涡轮子午流道设计与功率分配方法,综合分析了多级低压涡轮功率分配需要考虑的各项因素,并探讨了高升力涡轮叶型设计方法。研究表明:过渡流道方案设计可以采用长高比及当量扩张角作为初步选取标准;多级低压涡轮功率分配要综合考虑不同工况性能及气动设计参数;完成设计的大转折角后加载叶型能够有效地控制涡轮叶栅内的流动损失。

Aerodynamic Design of Multistage Low Pressure Turbine for High Bypass Ratio Aeroengine

The aerodynamic design charactersitics, design selection criterion of main parameters and development trends of the high bypass ratio aeroengine multistage Low Pressure Turbine (LPT) were analyzed based on the investigation of the high bypass ratio aeroengine multistage LPT. The selection criterion and optimization design method of inter turbine duct design parameter, the meridional channel design and power distribution methods of LPT were investigated. The power distribution of each stage were analyzed comprehensively and the design methods of high lift turbine airfoil were dicussed. The result shows that the inter turbine duct design can use aspect ratio and equivalent expansion angle as a preliminary selection criteria. The different condition performance and aerodynamic design parameters are considered for the multistage turbine power distribution. The design of large turning angle loaded turbine airfoil can effectively control the flow loss in turbine cascade.