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Local Nonlinear Control of Stall Inception in Axial Flow Compressors

dc.contributor.authorAdomaitis, Raymond A.en_US
dc.contributor.authorAbed, Eyad H.en_US
dc.date.accessioned2007-05-23T09:53:55Z
dc.date.available2007-05-23T09:53:55Z
dc.date.issued1993en_US
dc.identifier.urihttp://hdl.handle.net/1903/5385
dc.description.abstractA combination of theoretical and computational nonlinear analysis techniques are used to study the scenario of bifurcations responsible for the initiation of rotating stall in an axial flow compressor model. It is found that viscosity tends to damp higher-frequency modes and so results in a sequence of bifurcations along the uniform-flow solution branch to stall cells of different mode number. Lower-mode stalled flow solutions are born in subcritical bifurcations, meaning that these equilibria will be unstable for small amplitudes. Secondary bifurcations, however, can render them stable, leading to hysteresis. Using throttle position as a control, we find that while the stall bifurcations are not linearly stabilizable, nonlinear state feedback of the first mode amplitude will reduce the hysteresis. This improves the nonlinear stability of the compression system near the stall margin.en_US
dc.format.extent573697 bytes
dc.format.mimetypeapplication/pdf
dc.language.isoen_USen_US
dc.relation.ispartofseriesISR; TR 1993-40en_US
dc.subjectaircraften_US
dc.subjectdistributed parameter systemsen_US
dc.subjectnonlinear systemsen_US
dc.subjectstabilityen_US
dc.subjectIntelligent Servomechanismsen_US
dc.titleLocal Nonlinear Control of Stall Inception in Axial Flow Compressorsen_US
dc.typeTechnical Reporten_US
dc.contributor.departmentISRen_US


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