高负荷低速轴流风扇数值优化设计与实验研究

推进技术 ›› 2009, Vol. 30 ›› Issue (6): 696-702.

高负荷低速轴流风扇数值优化设计与实验研究

金东海,李泯江,桂幸民

北京航空航天大学能源与动力工程学院;上海宇航系统工程研究所;北京航空航天大学能源与动力工程学院

发布日期:2021-08-15
基金资助:
国家自然科学基金(50136010,50676004)

Numerical design optimization of a high-loaded low-speed axial-flow fan and experimental research

Coll.of Energy and Power Engineering, Beijing Univ.of Aeronautic and Astronautics, Beijing 100191, China;Aerospace System Engineering Inst.,Shanghai 201108, China;Coll.of Energy and Power Engineering, Beijing Univ.of Aeronautic and Astronautics, Beijing 100191, China

Published:2021-08-15

摘要/Abstract

摘要： 应用基于自适应遗传算法和复合形法发展的混合遗传算法数值设计平台ADOP,对某高负荷低速轴流风扇TA36A实施气动数值优化。该风扇设计转速2.9kr/min,三维数值结果近设计点流量7.482kg/s,绝热效率为84.54%,失速裕度为16.38%;优化设计后风扇TA36B数值模拟结果失速裕度提高了1.6个百分点,气动效率为85.31%,比原型略有提高。气动性能试验风扇TA36B失速裕度达18.84%,具有较宽的稳定工作范围。

关键词: 航空发动机;压气机;风扇;遗传算法+;优化设计;数值仿真

Abstract: A high-loaded low-speed axial-flow fan was optimized based on ADOP, which is developed by hybrid genetic algorithm based on adaptive genetic algorithm and complex method. The design speed of TA36A is 2.9 kr/min. 3D numerical simulation results show that the isentropic efficiency is 84.54% and the stall margin is 16.38%, when the mass flow rate is 7.482 kg/s nearby the design point. After optimization, the stall margin of TA36B is increased by 1.6% and the isentropic efficiency is 85.31%, a little higher than the original one. The aerodynamic experimental results of TA36B show that the stall margin is 18.84%, which proves a wide stall margin.

Key words: Aircraft engine;Air compressor;Fan;Genetic algorithm+;Optimum design;Numerical calculation

金东海,李泯江,桂幸民. 高负荷低速轴流风扇数值优化设计与实验研究[J]. 推进技术, 2009, 30(6): 696-702.