Unsteady Fluid Dynamic Response of an Axial-Flow Compressor Stage with Distorted Inflow
PURDUE UNIV LAFAYETTE IN PROJECT SQUID HEADQUARTERS
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A nonlinear, large disturbance theory has been developed which couples, interactively, the flow through the blade passages of a turbomachine blade row and an axially distorted flow field. The blade row analysis is based on the time-dependent energy equation of the flow through the passage and includes a nonlinear description of cascade loss and turning correlations from available experimental sources. The flow field analysis involves the nonlinear, time-dependent equations for the vorticity and the stream function. Coupling of the two is accomplished through the boundary conditions by mutual relationships between the pressure change across the blade row and the change in vorticity in the flow field analyses. Within the assumptions that the flow is two- dimensional and incompressible, the numerical solution is capable of predicting the influence of an upstream axial distortion on the onset of a circumferentially rotating stall pattern for a single blade row. The speed of rotation of the stall cell and the spatial attenuation of the distortion wave are also predicted, and although the observed experimental data are generally available only for multistage systems, the predicted results for the single blade row are in qualitively good agreement with the data.
- Fluid Mechanics
- Jet and Gas Turbine Engines