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A numerical simulation of a 1.5 stages high pressure axial compressor is presented. The effect of casing suction on compressor aerodynamic performance, stage matching as well as flow loss is discussed in detail. Using modern CFD codes Numeca/FINE, the 3D steady flow inside the 1.5 stages axial compressor has been simulated and visualized, respectively at cruise speed and maximum climbing speed. Numerical solutions show that casing suction partly removes the low-momentum fluid and reduces the flow blockage at tip region, thus improves stage matching mildly between rotor and stator. In general, casing suction, which provides main flow for flight air system, has slight impact on compressor blade row performance and loss characteristics.

Effect of Casing Suction on Stage Matching and Flow Loss in a High Pressure Axial Compressor