Spatially resolved compressor characteristics for modeling and control of blade-scale flow instabilities

Raymond A. Adomaitis

doi:10.1117/12.210517

30 May 1995 Spatially resolved compressor characteristics for modeling and control of blade-scale flow instabilities

Raymond A. Adomaitis

Proceedings Volume 2494, Sensing, Actuation, and Control in Aeropropulsion; (1995) https://doi.org/10.1117/12.210517
Event: SPIE's 1995 Symposium on OE/Aerospace Sensing and Dual Use Photonics, 1995, Orlando, FL, United States

Abstract

A numerical technique capable of simulating blade-scale compression system flow instabilities over time-scales spanning tens of rotor revolutions is presented. Simulations of stall inception, growth to fully developed rotating stall, and evidence for hysteresis, secondary instabilities, and other nonlinear phenomena are presented. Signal processing techniques for flow asymmetry characterization are discussed in the context of obtaining low-order representations of the flow disturbances with the ultimate goal of active stall suppression.

Citation Download Citation

Raymond A. Adomaitis "Spatially resolved compressor characteristics for modeling and control of blade-scale flow instabilities", Proc. SPIE 2494, Sensing, Actuation, and Control in Aeropropulsion, (30 May 1995); https://doi.org/10.1117/12.210517

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