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Dimension Determination of Precursive Stall Events in a Single Stage High Speed CompressorThis paper presents a study of the dynamics for a single-stage, axial-flow, high speed compressor core, specifically, the NASA Lewis rotor stage 37. 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 the stall margin. 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 box-assisted correlation dimension methodology, 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 undesirable event of rotating stall formation in high speed compressor cores.
Document ID
19960047991
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Bright, Michelle M. (NASA Cleveland, OH United States)
Qammar, Helen K. (Akron Univ. Akron, OH United States)
Hartley, Tom T. (Akron Univ. Akron, OH United States)
Date Acquired
September 6, 2013
Publication Date
July 14, 1996
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
E-10335
NASA-TM-107268
NAS 1.15:107268
Meeting Information
Meeting: Technical Conference on Nonlinear Dynamics and Full Spectrum Processing
Location: Mystic, CT
Country: United States
Start Date: July 10, 1995
End Date: July 14, 1995
Sponsors: Office of Naval Research
Accession Number
96N33509
Funding Number(s)
PROJECT: RTOP 505-62-50
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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