A compressor-face boundary condition that models the unsteady interactions of acoustic and convective velocity disturbances with a compressor has been implemented into a three-dimensional computational fluid dynamics code. Locally one-dimensional characteristics along with a small-disturbance model are used to compute the acoustic response as a function of the local stagger angle and the strength and direction of the disturbance. Simulations of the inviscid flow in a straight duct, a duct coupled to a compressor, and a supersonic inlet demonstrate the behavior of the boundary condition in relation to existing boundary conditions. Comparisons with experimental data show a large improvement in accuracy over existing boundary conditions in the ability to predict the reflected disturbance from the interaction of an acoustic disturbance with a compressor.

Issue Section:
Technical Papers
Keywords:
compressors, aerodynamics, convection, turbines, acoustic waves, fluid dynamics
Topics:
Acoustics, Boundary-value problems, Compressors, Pressure, Blades, Flow (Dynamics)
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Copyright © 2001
 by ASME
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