摘要
在某涡扇发动机结构优化中,为满足总体结构和机械系统的要求,采用了兼具支板功能的紧凑式低压涡轮导向器设计方案。在完成常规涡轮设计的基础上,通过子午流道设计和大叶片设计及数值仿真,对导向器内的流动进行了细致而有效的控制,并对其进行了三轮优化设计和流场分析。结果表明,该优化设计方案在满足结构设计要求的同时保持了良好的气动性能,具有明显的先进性,并在发动机整机试验中取得了良好效果,可推广到其它发动机研制和改型设计中。
According to the turbofan engine structure optimization design, a compact low pressure turbine nozzle with the function of the strut was adopted to meet the requirements of general structure and mechani- cal system. On the basis of conventional turbine design, the flow inside of nozzle was effectively controlled by means of meridian flowpath, large vane design and numerical simulation; and three rounds of optimiza- tion design and flowfield analysis were accomplished. The results show that this scheme meets the structur- al requirements with favorable performance, and represents famous result in the engine test that could be generalized in the development and derivative design of other models.
出处
《燃气涡轮试验与研究》
北大核心
2013年第2期12-17,共6页
Gas Turbine Experiment and Research
关键词
紧凑式低压涡轮导向器
航空发动机
匹配性能
周向不均匀度
子午流道
叶片造型
compact low pressure turbine nozzle
aero-engine
matching performance
circumferential asymmetry
meridian flowpath
airfoil profile
