Abstract
An experimental and computational research program has been performed to study the effects of stator indexing (clocking) in a high-speed axial compressor stage with an inlet guide vane. The work is directed at determining the basic flow mechanisms causing the performance variations associated with airfoil clocking. A comparison of the results obtained for two axial gaps between the rotor and the stator has been carried out to determine the role of potential interaction between blade rows as the airfoils are clocked.
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