Attractor dimension analysis of a single-stage high-speed compressor

Michelle M. Bright; Helen K. Qammar; Tom T. Hartley

doi:10.1117/12.210513

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30 May 1995 Attractor dimension analysis of a single-stage-high-speed compressor

Michelle M. Bright; Helen K. Qammar; Tom T. Hartley

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Proceedings Volume 2494, Sensing, Actuation, and Control in Aeropropulsion; (1995) https://doi.org/10.1117/12.210513
Event: SPIE's 1995 Symposium on OE/Aerospace Sensing and Dual Use Photonics, 1995, Orlando, FL, United States

Abstract

This paper presents a study of the dynamics for a single-stage, high-speed compressor core, specifically, the NASA Lewis rotor stage 35. Due to the overall blading design for this advanced core compressor, each stage has considerable tip loading and higher speed than most compressor designs, thus the compressor operates closer to stall. Due to the operation of this compressor close to the stall line, it is important to quickly predict the onset of stall. The onset of rotating stall is explained as bifurcations in the dynamics of axial compressors. Data taken from the compressor during a rotating stall event is analyzed. Through the use of a dimension analysis technique, the attractor dimension is determined during the bifurcations leading to rotating stall. The intent of this study is to examine the behavior of precursive stall events so as to predict the entrance into rotating stall. This information may provide a better means to identify, avoid, or control the catastrophic event of rotating stall formation in high-speed compressor cores.

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Michelle M. Bright, Helen K. Qammar, and Tom T. Hartley "Attractor dimension analysis of a single-stage-high-speed compressor", Proc. SPIE 2494, Sensing, Actuation, and Control in Aeropropulsion, (30 May 1995); https://doi.org/10.1117/12.210513

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