Abstract
Abstract
The influence of different tip clearance shapes on aerodynamic performance of an axial-flow compressor stator under the condition of both stationary and rotating hub was investigated by a numerical method. In this paper, the calculations are based on the three-dimensional Navier-Stokes equations expressed with non-orthogonal curvilinear coordinates and corresponding non-orthogonal velocity components, and the explicit time marching algorithm and Baldwin-Lomax turbulence model are adopted. The clearance shapes considered in this paper include large and small uniform tip clearance, expanding and shrinking tip clearance from the blade leading edge to the trailing edge along the axial direction. The analysis of computed results shows, at least for the test cases in this paper, that tip leakage vortex was found to be generated earlier for stationary hub cases than for rotating hub cases. On the same working conditions and within a certain range of clearance scale, the blade row with smaller tip clearance height can attain higher efficiency, and for the same circumferential leakage area, the blade row with expanding tip clearance was found to have higher efficiency.
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