Inception and development of multiple stall cells of short length scales are numerically
investigated in an axial compressor rotor blade row. The method of investigation is based
on time accurate three-dimensional full annulus simulations. Time dependent flow structure
results revealed that there are two criteria responsible for inception of a special kind of
stall, introduced as spike stall in the literature. These criteria are defined as leading edge
spillage and trailing edge backflow, which occur at specific mass flow rates near to stall
conditions. The numerical results revealed that once the spike stall cells appear, they cover
roughly two blade passages in the circumferential direction and cover about 25% of the blade
height. By further revolution of the blade row, the number of cells tends to increase. For
the present case study, the number of stall cells increased to three after 8.5 rotor revolutions
from the moment of the initial spike stall occurrence. Even at this moment, both of the
above mentioned criteria for the spike stall inception have been observed within the blades
passages. These events caused the inlet relative flow angle to the blade rows, and therefore the
flow incidence angle and consequent blockage to the main flow, to increase. The tip leakage
flow frequency spectrum has been studied through surveying instantaneous static pressure
signals imposed on pressure side of the blades and also on the casing walls. These latter
results showed that any further revolving of the rotor blade row, exceeding 8.5 revolutions,
causes the spike stall to disturb the flow structure significantly.
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