Three-dimensional 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 percent 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. [S0889-504X(00)00903-X]
Issue Section:
Technical Papers
Keywords:
compressors,
transonic flow,
vortices,
Navier-Stokes equations,
flow simulation,
Mach number,
finite volume methods
Topics:
Blades,
Compressors,
Displacement,
Flow (Dynamics),
Leakage,
Rotors,
Mach number,
Boundary layers,
Simulation,
Vortices
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19.
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, No. 2. Copyright © 2000
by ASME
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