摘要
针对某小型弹用涡扇发动机的设计需求,完成了由两级跨音速风扇与两级亚音速增压级组合的小涵道比多级风扇/增压级部件设计。根据所设计风扇/增压级的组合构型特点,采用风扇和增压级分别按照流程先完成设计再进行组合的设计思路,在设计中充分运用了轴流压气机设计体系、经验数据库及设计工具。在分别完成风扇和增压级的一维方案优选及S2流面通流设计的基础上,运用了任意中弧线叶型设计方法完成两级跨音风扇的转子叶片设计,选择经典的NACA系列叶型完成风扇静子及两级亚音速增压级的叶片设计。对所设计的小型多级风扇/增压级开展了部件性能试验验证,试验结果表明,风扇/增压级的流量、压比、效率及稳定裕度等各项性能设计指标均可满足。
In response to the design requirement of a small missile turbofan engine,a multi-stage fan/booster component with a small bypass ratio was designed,which consists of a two-stage transonic fan and a two-stage subsonic booster.Based on the characteristics of the configuration of the fan/booster combination,the fan and booster were designed separately,and then the two parts of the design were merged together.The axial flow compressor design methodology,experiential database,and design tools were fully utilized in the design.On the basis of the one-dimensional optimization of the fan/booster combination and the S2 flow surface flow design,the blade design of the two-stage transonic fan rotors was completed using any profile mean camber line blade design method.The classic NACA series blade was selected for the vanes of the fan and the two-stage subsonic booster.Experiments were conducted to test the performance of the designed small multi-stage fan/booster,and the result showed that the mass-flow rate,pressure ratio,efficiency,and stability margin and other critical parameters all met the requirement.
作者
周进
陈亮良
游群智
稂仿玉
冯兴
王涛
Jin Zhou;Liang-liang Chen;Qun-zhi You;Fang-yu Lang;Xing Feng;Tao Wang(Aecc Hunan Aviation Powerplant Research Institute;Hunan Key Laboratory of Turbomachinery on Small and Medium Aero-Engine;Aero Engine Corporation of China)
出处
《风机技术》
2025年第6期23-30,共8页
Chinese Journal of Turbomachinery
基金
湖南省科技创新计划项目(2024JK2055)。
