Exploring numerically overall performance and flow field of mixed flow compressor stage with splitter blades

Sections 1 and 2 brief our usual method of numerical exploration. Section 3 presents the simulation results of our exploration and their analysis; its core consists of two parts: the simulation results and their analysis. The simulation results are given in Table 1 and Figs. 3 through 16 but not including Fig. 7. The analysis of simulation results shows preliminarily that: (1) there are discrepancies between the simulation results and experimental data provided by others; (2) compared with the experimental data, the characteristic line of mass flow-pressure ratio moves up and toward the right side; (3) the characteristic line of mass flow-adiabatic efficiency moves up and towards the right side; (4) there are low-velocity stagnation zones near the shroud areas at the outlets of two blade passages of the mixed flow impeller under investigation in this paper; the stagnation zone of Blade Passage 1 is caused by the boundary layer displacement forced by the Coriolis force; the stagnation zone of Blade Passage 2 is caused by the blade tip leakage flow; (5) the stall of the high-pressure ratio mixed flow compressor is mainly caused by the stagnation zone in Blade Passage 1.