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When a compressor approaches its surge limit, some of its
components (diffusers, impeller) may start to operate in stall. Stall
occurs when the gas flow starts to separate from a flow surface
(Figure 1). Changing the operating point of a compressor always
involves a change in incidence angles for the aerodynamic
components. Just as with an airfoil (Figure 1), increasing the incidence
angle will eventually lead to stall. Stall in turbomachines often appears
as rotating stall, when localized regions of separated flow move along
the diffuser at speeds below the rotational speed of the impeller (Day,
1991). Surge is the ultimate result of system instability.
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