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Ice accretion is a phenomenon where super-cooled water droplets impinge and accrete on a body. It occurs frequently on airplanes, windmills and conductor cables. In particular, when ice layer is formed on an aircraft wing, it affects on the aerodynamic performance by increasing drag and reducing lift, and it may cause a serious accident. On a jet engine, ice accretion disturbs the inlet flow, and separated ice pieces can damage to the compressor and the casing, which leads to the severe performance degradation. There have been several accidents due to ice accretion. Therefore, the estimation of ice accretion is necessary to avoid accidents. In this study, the authors simulate icing phenomena in rotor-stator cascade considering rotor tip clearance. The numerical results indicate that the leakage vortex generated by the tip clearance changes the flow field and droplet motions, and consequently the changes makes accreted ice on the stator vane surface decrease.

NUMERICAL INVESTIGATION OF TIP CLEARANCE EFFECT OF ICING IN ROTOR/STATOR INTERACTION