| 史磊1，林文俊2，黄晨雷3，马龙1，于满1.前缘缺口型损伤风扇转子叶栅流动特性分析[J].航空发动机,2022,48(5):73-79 |
| Analysis of Flow Characteristics of Fan Rotor Cascade with Leading Edge Notch Damage |
| DOI： |
| Key Words:fan rotor airfoil leading edge notch damage cascade flow characteristics aeroengine |
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| Abstract:In order to study the influence of the blade profile deformation on the compressor performance after encountering the foreign
object damage on the fan rotor blade，numerical simulation was carried out for the compressor blade with notch damage at the leading edge，
the overall aerodynamic characteristics and the variation details of the internal flow field were analyzed. A cascade model was established
based on the 50% span airfoil of the fan blade from a small high bypass ratio turbofan engine. It was assumed that the middle section of the
cascade was impacted on the leading edge by a spherical particle and a notch damage with a depth of 1.2% chord length and a width of
2.5% blade height was formed at the leading edge. With the help of NUMECA Fine/Open software package，a full-channel linear cascade
numerical simulation of the 50% span fan blade airfoil with leading edge notch damage was carried out. The region investigated includes
six cascade passages. The changes of aerodynamic characteristics and internal flow field structure of the cascade before and after damage
were analyzed quantitatively. The results show that at Mach number 0.6，the leading edge notch damage increases the total pressure loss co?
efficient of the airfoil across the whole range of angle of attack，with the maximum of 3.11%. The diffusion factor increases up to 13.5% af?
ter leading edge damage. |
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