Investigation on centrifugal impeller in an axial-radial combined compressor with inlet distortion |
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Authors: | Du Li Ce Yang Ben Zhao Mi Zhou Mingxu Qi Jizhong Zhang |
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Affiliation: | (1) Department of Aerospace Engineering, Middle East Technical University, 06531 Ankara, Turkey;(2) Department of Mechanical Engineering, The Johns Hopkins University, 3400 N. Charles St., 21218 Baltimore, MD, USA |
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Abstract: | Assembling an axial rotor and a stator at centrifugal compressor upstream to build an axial-radial combined compressor could
achieve high pressure ratio and efficiency by appropriate size augment. Then upstream potential flow and wake effect appear
at centrifugal impeller inlet. In this paper, the axial-radial compressor is unsteadily simulated by three-dimensional Reynolds
averaged Navier-Stokes equations with uniform and circumferential distorted total pressure inlet condition to investigate
upstream effect on radial rotor. The results show that span-wise nonuniform total pressure distribution is generated and radial
and circumferential combined distortion is formed at centrifugal rotor inlet. The upstream stator wake deflects to rotor rotation
direction and decreases with blade span increases. Circumferential distortion causes different separated flow formations at
different pitch positions. The tip leakage vortex is suppressed in centrifugal blade passages. Under distorted inlet condition,
flow direction of centrifugal impeller leading edge upstream varies evidently near hub and shroud but varies slightly at mid-span.
In addition, compressor stage inlet distortion produces remarkable effect on blade loading of centrifugal blade both along
chordwise and pitchwise. |
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Keywords: | axial-radial combined compressor centrifugal impeller wake inlet distortion |
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