Research on influence of radial total pressure distortion on forward and backward fan flow

Abstract

Abstract:

Modelling and simulation are used to study a small turbofan engine with high bypass ratio. With four situations of inlet total pressure distortion of equivalent surface of sector angles 60°, 90°, 120°and 150°, the influence of inlet radial total pressure distortion on forward and backward fan flow of turbofan engine is studied. It is found that the total pressure distortion index is bigger for backward fan part, and it is proved that the unstable level of backward fan part is bigger than forward fan part because of fan rotation; compared with tangential speed and axial speed,the radial speed distortion support is influenced more by inlet radial total pressure distortion; for the flow field of forward fan part, the total pressure distortion has the same type of increase for the four different inlet situations,but it is not the same for backward fan part which has the biggest value area.

Key words: turbofan-engine, radial total pressure distortion, distortion index, modelling and simulation

CLC Number:

V231.3

DENG Tian, LEI Pan, GAO Xuwan, WU Yuhao. Research on influence of radial total pressure distortion on forward and backward fan flow[J]. .

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