某高负荷子午加速风机气动设计与数值模拟

金海良; 金东海; 彭泽琰; 桂幸民

某高负荷子午加速风机气动设计与数值模拟

北京航空航天大学能源与动力工程学院, 航空发动机数值仿真研究中心, 北京 100191

基金项目: 国家自然科学基金(50676004,50736007)

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- 文章访问数: 1459
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- 被引次数: 0
出版历程
- 收稿日期: 2010-07-01
- 修回日期: 2010-10-15
- 刊出日期: 2011-07-28

Aerodynamic design and numerical investigation of a highly loaded meridian acceleration fan

Aeroengine Numerical Simulation Research Center,School of Jet Propulsion, Beijing University of Aeronautics and Astronautics,Beijing 100191,China

摘要

摘要: 兼顾民用风机的气动性能与制造成本,采用三种方案(等厚度串列静子方案、叶型串列静子方案和等厚度单排静子方案)对某高负荷子午加速风机进行了气动设计和数值模拟研究.结果表明采用叶型叶片与等厚度叶片相比对风机气动性能的改善很小,近设计点时叶型串列静子方案的压比和效率仅比等厚度串列静子方案高0.18%和0.8%.串列静子抑制了单排静子通道内的角区分离,减小了通道内的堵塞,使等厚度串列静子方案的失速裕度比等厚度单排静子方案提高了11%.综合考虑气动性能与制造成本选定等厚度串列静子方案为风机的最终方案,其不同转速的特性表明该方案的性能完全满足设计指标的要求.
- 高负荷 /
- 子午加速 /
- 风机 /
- 串列叶片 /
- 气动设计
Abstract: Considering the aerodynamic performance and manufacturing cost of civil fan,the aerodynamic design and three-dimensional numerical investigation of a highly loaded meridian acceleration fan were performed using three design schemes (uniform thickness tandem stator scheme,airfoil tandem stator scheme and uniform thickness single row stator scheme).The results indicate that the utilization of airfoil blade has few improvements on aerodynamic performance.The total pressure ratio and adiabatic efficiency of the airfoil tandem stator scheme are increased only by 0.18% and 0.8% respectively compared with the uniform thickness tandem stator scheme at near design point.The stall margin of the uniform thickness tandem stator scheme is increased by 11% than the uniform thickness single row stator scheme due to the suppression of the corner separation in the single row stator passage and the reduction of the passage blockage by the tandem stator.Considering aerodynamic performance and manufacturing cost the uniform thickness tandem stator scheme is selected as the final scheme of the fan and its performance characteristics at different rotating speeds can satisfy the design requirements.
- highly loaded /
- meridian acceleration /
- fan /
- tandem blade /
- aerodynamic design

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参考文献(15)

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