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某高负荷子午加速风机气动设计与数值模拟
引用本文: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[J].航空动力学报,2011,26(7):1638-1646.
作者姓名:金海良  金东海  彭泽琰  桂幸民
作者单位: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)
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...

关 键 词:高负荷  子午加速  风机  串列叶片  气动设计
收稿时间:7/1/2010 5:52:42 PM
修稿时间:2010/10/15 0:00:00

Aerodynamic design and numerical investigation of a highly loaded meridian acceleration fan
JIN Hai-liang,JIN Dong-hai,PENG Ze-yan and GUI Xing-min.Aerodynamic design and numerical investigation of a highly loaded meridian acceleration fan[J].Journal of Aerospace Power,2011,26(7):1638-1646.
Authors:JIN Hai-liang  JIN Dong-hai  PENG Ze-yan and GUI Xing-min
Institution:Aeroengine Numerical Simulation Research Center,School of Jet Propulsion, Beijing University of Aeronautics and Astronautics,Beijing 100191,China;Aeroengine Numerical Simulation Research Center,School of Jet Propulsion, Beijing University of Aeronautics and Astronautics,Beijing 100191,China;Aeroengine Numerical Simulation Research Center,School of Jet Propulsion, Beijing University of Aeronautics and Astronautics,Beijing 100191,China;Aeroengine Numerical Simulation Research Center,School of Jet Propulsion, Beijing University of Aeronautics and Astronautics,Beijing 100191,China
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 indicated that the utilization of airfoil blade has little improvement on aerodynamic performance. The total pressure ratio and adiabatic efficiency of the airfoil tandem stator scheme increased only by 0.18% and 0.8% respectively compared to 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. The uniform thickness tandem stator scheme was selected as the final scheme of the fan considering aerodynamic performance and manufacturing cost and its performance characteristics at different rotating speeds can satisfy the design requirements.
Keywords:highly loaded  meridian acceleration  fan  tandem blade  aerodynamic design
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