Influence of Complex Inlet Boundary on HighPressure&nbsp; Stage Compressor Performance

XIAO Xiangyu; MA Chaochen; SHI Xin; ZHANG Hang

doi:10.3969/j.issn.1001-2222.2020.06.002

Vehicle Engine ›› 2020, Vol. 0 ›› Issue (6) : 7-12. DOI: 10.3969/j.issn.1001-2222.2020.06.002

Influence of Complex Inlet Boundary on HighPressure Stage Compressor Performance

XIAO Xiangyu，MA Chaochen，SHI Xin，ZHANG Hang

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Abstract

The model of highpressure stage compressor with interstage pipeline was established and the flow field changes of downstream highpressure stage compressor were compared and analyzed under uniform and nonuniform inlet conditions. The results show that the obvious circumferential distortion occurs at the inlet of high-pressure compressor and the pressure distributes in the form of high outside and low inside, no matter whichever the inlet boundary condition is. There were also some flow vortices at the transition between the bend and straight pipes, indicating that the circumferential distortion at the inlet of highpressure compressor was mainly caused by its twistedshape pipeline. Moreover, it was found that the flow field at 50% span was obviously affected by the uneven circumferential pressure field caused by the volute tongue through the analysis of flow field between the blades of compressor. The high entropy areas formed on the left side of volute tongue possibly because the blocked flow led by the high static pressure resulted in flow separation on the left side of the volute tongue. Besides, the effect of volute tongue weakened at 90% span and the loss caused by the tip leakage flow was more obvious.

Key words

two-stage turbocharging / centrifugal compressor / flow distribution / distortion / numerical calculation

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XIAO Xiangyu，MA Chaochen，SHI Xin，ZHANG Hang. Influence of Complex Inlet Boundary on HighPressure Stage Compressor Performance[J]. Vehicle Engine. 2020, 0(6): 7-12 https://doi.org/10.3969/j.issn.1001-2222.2020.06.002