前缘侵蚀对民航发动机风扇/增压级气动特性的影响研究
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1.中国民航大学航空工程学院;2.中国民航大学中欧航空工程师学院;3.中国商飞 上海飞机设计研究院;4.西交利物浦大学智能工程学院;5.厦门航空有限公司发动机管理中心

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V231.3

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翼型-叶栅空气动力学国家重点实验室开放基金(6142201200509);民航航空器适航审定技术重点实验室开放基金(SH2022070501)


Study of the effect of leading edge erosion on the aerodynamic characteristics of fan/booster stages of civil aviation engines
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Aeronautical Engineering Institute, Civil Aviation University of China

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    摘要:

    为了分析风扇转子叶片前缘侵蚀对压缩系统不同内外涵工况气动特性的影响,本文通过多级联算数值分析了某型大涵道比发动机压缩系统气动特性变化。研究结果表明,在峰值效率点工况下,前缘侵蚀后的发动机压缩系统总压比、等熵效率和通道流量分别相对下降0.18%、0.879%和0.972%。对风扇转子叶片而言,前缘侵蚀导致外涵道近喘点工况下95%叶高处表面静压系数曲线轴向0-24%区间的斜率下降,静压降低,轴向24%-40%区间的斜率上升,使叶型负荷降低,增压能力下降,激波向前移动。此外,前缘侵蚀会使外涵道近喘点处整体风扇叶片的攻角增大2°左右,导致叶片气动效率和失速裕度产生变化,偏离原始叶型设计。

    Abstract:

    In order to analyze the effect of fan rotor blade leading edge erosion on the aerodynamic characteristics of the compression system for different internal and external culverting conditions, multilevel cascade calculations were used to investigate the changes in the aerodynamic characteristics of the compression system of a certain type of engine with large culverting ratio. The results show that the total pressure ratio, isentropic efficiency and channel flow rate of the engine compression system after leading edge erosion relatively decrease by 0.18%, 0.879% and 0.972%, respectively, under the peak efficiency point working condition. For fan rotor blades, leading edge erosion leads to a decrease in the slope of the surface static pressure coefficient curve in the axial 0-24% interval of the surface static pressure coefficient curve at the height of 95% of the blades under near-surge point conditions in the outer culvert channel, with a decrease in static pressure, and an increase in the slope in the axial 24-40% interval, which reduces the loading of the blade, reduces the pressurizing capacity, and moves the surge wave forward.In addition, leading edge erosion increases the angle of attack of the overall fan blade at the near-surge point of the outer culvert by about 2°, resulting in changes in blade aerodynamic efficiency and stall margin, which deviates from the original blade design.

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蔡润峰,史磊,姜瑞麟,等. 前缘侵蚀对民航发动机风扇/增压级气动特性的影响研究[J]. 科学技术与工程, , ():

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  • 收稿日期:2024-03-08
  • 最后修改日期:2024-04-16
  • 录用日期:2024-04-25
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