单级轴流大小叶片压气机非定常流场数值研究

李海鹏; 刘火星; 蒋浩康

单级轴流大小叶片压气机非定常流场数值研究

北京航空航天大学能源与动力学院航空发动机气动热力重点实验室, 北京 100083

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出版历程
- 收稿日期: 2005-12-02
- 修回日期: 2006-03-23
- 刊出日期: 2006-12-28

Unsteady flow analysis of a single-stage compressor with splitter vane using numerical method

School of Jet Propulsion, Beijing University of Aeronautics and astronautics, Nutional Key Laboratory on Aero-Engines, Beijing 100083, China

摘要

摘要: 通过数值模拟方法对单级轴流大小叶片压气机与常规叶栅压气机的非定常压力场进行分析与对比,结果表明:由于小叶片的分隔效应,使得转子通道的非定常压力和单叶片非定常负荷脉动大大增强,并促进了压力波向上游的传播;但转、静子单元的整体扭矩和轴向力脉动降低;绝对坐标系下转子入口处的压力波动是转子势扰动、动静干扰产生的压力波和此波在周向的不均匀性的综合作用,不同的入口周向位置,压力波的幅值相位存在较大差别,小叶片的存在强化了这种差别。
- 航空、航天推进系统 /
- 大小叶片 /
- 单级轴流压气机 /
- 三维非定常 /
- 压力波动
Abstract: The numerical method was applied to the unsteady flow analysis of a single-stage compressor with splitter vane.The result shows that because of the separation effect of the splitter vane,the unsteady pressure fluctuation and unsteady blade load fluctuation are strengthened greatly,and it hastens the pressure wave spreading upstream,while the torque and axial force fluctuation of the rotor and stator unit are reduced.The pressure wave at the rotor inlet in the absolute coordinate is the integration of the potential disturb of the rotor,the pressure wave of the rotor-stator interaction and the circumferential distribution of this pressure wave.The magnitude of pressure wave in different circumferential position differs greatly,splitter vane strengthens this difference.
- aerospace propulsion system /
- splitter vane /
- single-stage compressor /
- 3D unsteady /
- unsteady pressure

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参考文献(9)

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