Abstract
The variable inlet guide vane (VIGV) and front stage variable stator vanes (VSV) are widely used among multistage axial compressors to improve compressor aerodynamic performance for both gas turbine and aircraft engine. In this paper, the effects of IGV variability on the aerodynamic performance of a 1.5-stage transonic axial compressor at design speed are studied by three-dimensional numerical simulation. After simulating seven IGV angles (-20°, -15°, -10°, -5°, 0°, +5°, +10°) respectively, it was found that the peak efficiency first increases and then decreases with the opening of IGV stagger angle, reaching the maximum when the IGV is -5°. The mass flow rate and total pressure ratio corresponding to the peak efficiency point increase. Detailed flow fields at peak efficiency point with different IGV angles are described and analysed to study the influence of IGV variability on the transonic rotor and even the stator. The work in this paper may give guidance for design of transonic axial compressor stage and also determination of the operation of 1.5 stage transonic compressor with VIGV.
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