Numerical investigation of flow field prediction for a subsonic three-stage compressor under a design condition based on dissipation weighting analysis

Abstract

The flow field in a multistage compressor is complex and the loss evolution mechanism of each stage requires further study. A subsonic three-stage compressor designed by the authors’ team was used as the research object. The applicability of the total pressure loss weighting analysis method based on a vortex structure in a stage environment was discussed, and then, the operability of a dissipation weighting processing method based on Ω–V_db extraction was discussed. This method has wider applicability and provides more accurate extraction data. The evolution law of the flow loss of the rotor and stator blades at all stages of the compressor under the design conditions was studied. Further, the complete three-stage dissipation weighting was extracted using this method, and the dissipation of the rotor in the first and second stages, from the shroud dissipation property as the dominant factor, to the profile dissipation property as the dominant factor (27.3 %, 32.57 %), was analyzed. The results indicate that dissipation migration (32.11 %, 49.13 %) of the suction side of the first- and second-stage stator blades is the main development law of the design condition. Finally, the flow field of the compressor from the design point to the near-stall condition is accurately predicted, and a flow-field optimization strategy for the design point is provided.