The effects of high steady loading and separated flow on the unsteady aerodynamic response of turbomachine blade rows are experimentally investigated. This is accomplished utilizing a unique single stage turbomachine research facility in which the flow is not generated by the blading but rather by an additional fan. Thus, for a particular stator incidence angle, the steady or mean stator aerodynamic performance were determined in a completely steady flow with no rotor and also with unsteady flow generated by a rotor composed of perforated plates at the same mean operating condition, thereby identifying the stator vane row dynamic stall conditions. The unsteady aerodynamic response of the very low solidity stator vane row is then investigated over a range of incidence angle values, including attached and separated flows with dynamic stall.

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