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Active unsteady aerodynamic suppression of rotating stall in an incompressible flow centrifugal compressor with vaned diffuserA mathematical model is developed to analyze the suppression of rotating stall in an incompressible flow centrifugal compressor with a vaned diffuser, thereby addressing the important need for centrifugal compressor rotating stall and surge control. In this model, the precursor to to instability is a weak rotating potential velocity perturbation in the inlet flow field that eventually develops into a finite disturbance. To suppress the growth of this potential disturbance, a rotating control vortical velocity disturbance is introduced into the impeller inlet flow. The effectiveness of this control is analyzed by matching the perturbation pressure in the compressor inlet and exit flow fields with a model for the unsteady behavior of the compressor. To demonstrate instability control, this model is then used to predict the control effectiveness for centrifugal compressor geometries based on a low speed research centrifugal compressor. These results indicate that reductions of 10 to 15 percent in the mean inlet flow coefficient at instability are possible with control waveforms of half the magnitude of the total disturbance at the inlet.
Document ID
19910057021
Document Type
Conference Paper
Authors
Lawless, Patrick B. (Purdue Univ. West Lafayette, IN, United States)
Fleeter, Sanford (Purdue University West Lafayette, IN, United States)
Date Acquired
August 15, 2013
Publication Date
June 1, 1991
Subject Category
AERODYNAMICS
Report/Patent Number
AIAA PAPER 91-1898
Distribution Limits
Public
Copyright
Other