某涡扇发动机多级高负荷风扇/压气机气动性能数值模拟

金东海; 桂幸民

某涡扇发动机多级高负荷风扇/压气机气动性能数值模拟

北京航空航天大学能源与动力工程学院,北京 100191

基金项目: 国家自然科学基金(51006005,50736007); 中央高校基本科研业务费专项资金(YWF-10-02-013); “凡舟”青年科研基金(20100401)

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出版历程
- 收稿日期: 2010-09-28
- 修回日期: 2011-03-03
- 刊出日期: 2011-05-28

Numerical simulation of highly loaded multi-stage fan / compressor of a turbofan engine

School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 针对某涡扇发动机高空低雷诺数下的应用需求,利用Numeca三维数值模拟软件对其多级高负荷风扇/压气机进行地面0km及高空21km工况下各转速的气动性能评估和流场分析.结果表明:该4级风扇的三维数值模拟结果与实验结果吻合良好,仿真精度能够满足工程精度要求,从0km升至21km,风扇进口叶弦雷诺数从10⁶降至10⁵量级,风扇流量衰减2%~3%,压比略有降低,效率衰减3%;在9级压气机的三维数值模拟中,考虑了级间引气对气动性能的影响,从0km升至21km,压气机进口叶弦雷诺数同样从10⁶降至10⁵量级,流量和总压比略有降低,效率衰减随转速降低而增大,衰减量达4%~7%.
- 数值模拟 /
- 高负荷 /
- 风扇/压气机 /
- 气动性能 /
- 低雷诺数
Abstract: According to high-altitude and low Reynolds number aerodynamic performance requirements of a turbofan engine, the fan/compressor on 0km and 21km operating conditions were simulated using three-dimensional (3-D) numerical simulation software Numeca. The results show that: the three-dimensional numerical simulation results of the 4-stage fan are in good agreement with the experimental results, and the precision can meet the engineering requirements; from 0km to 21km altitude, the inlet blade chord Reynolds number is reduced from 10⁶ to 10⁵, the mass flow rate is reduced by 2%~3%, the total pressure ratio is decreased a bit, and the efficiency is decreased by 3%; in the 3-D numerical simulation of 9-stage compressor, air bleeding is considered; from 0km to 21km altitude, the inlet blade chord Reynolds number is also reduced from 10⁶ to 10⁵, the mass flow rate and total pressure ratio are decreased a bit, and the attenuation of adiabatic efficiency increases from 4% to 7% with the decrease of speed.
- numerical simulation /
- highly loaded /
- fan/compressor /
- aerodynamic performance /
- low Reynolds number

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参考文献(13)

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