An Actuator Disk Analysis of an Isolated Rotor with Distorted Inflow.

摘要

An analytical study of the passage of distorted flow through an isolated, high hub-tip ratio axial compressor is reported. The analysis involves the coupling of the unsteady blade row aerodynamic response (with the flow immediately upstream of the blade row prescribed) with the unsteady duct flow both upstream and downstream of the blade row under the influence of the blade row loading. The numerical solution uses a starting procedure which does not require the inlet plane to be far enough upstream to be unaffected by the presence of the blade row. Hence any experimentally determined distortion at any arbitrary distance upstream of the blade row can be modelled. The results obtained indicate that the predicted pressure profile at the blade row exit is strongly dependent on the experimentally determined steady-state loss and exit flow angle curves, but is almost independent of the magnitude of the first order lag coefficient used to represent the boundary layer time delay through the blade passages. (Author)