Abstract
The operational environment of highly loaded helium compressor necessitates characteristics with narrow flow passages and short blade heights. These characteristics result in more prominent blade tip clearance leakage issues and stronger wake effects compared to air compressors. This study aims to clarify the separation flow structure and the spatiotemporal evolution mechanism of the highly loaded helium compressor cascade and to provide technical support for the aerodynamic stability optimization of such compressors. The present study investigated the effect of the relative positions of the upstream blade wake and downstream blade on cascade loss and separation characteristics of the highly loaded helium compressor with numerical and experimental analysis. The results demonstrate that the proportion of secondary flow losses, including tip leakage vortex of the downstream blade, is the lowest when the circumferential distance between the upstream inlet guide vane wake and the downstream rotor leading edge is 0.5 pitch, with an overall loss weight of 10.8% at the outlet section. Moreover, the proportion of secondary flow losses, including tip leakage vortex of the downstream rotor, is the highest when the circumferential distance between the upstream guide vane wake and downstream rotor leading edge (suction surface side) is 0.25 pitch. The overall loss weight at the outlet section for this position is 21.7%, which is twice that when the circumferential distance is 0.5 pitch. In addition, it can be demonstrated that tip leakage vortex plays a dominant role in vortex losses across all relative positions of the blades.
Published Version
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