3D multistage Navier-Stokes simulations for compressor components, rigs and cascades have been analyzed to gain insight into the tip leakage blockage evolution. From pitch-averaged flow quantities the local displacement caused by tip leakage is determined by means of a novel technique. Close to the throat an additional displacement of about 1–4% axial chord is observed for unchoked flow conditions. With tip gap height, stagger and inlet Mach number as governing variables a correlation for the tip leakage blockage transition function in blade passages is established, which may be used to improve the predictive capability of S1/S2 compressor aerodesign systems.

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