A rational basis for circumferential distortion index formulation
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Authors
Downs, Charles Patrick
Subjects
Compressor stall
Compressor surge
Compressor instability
Distortion index
Vorticity
Compressor surge
Compressor instability
Distortion index
Vorticity
Advisors
Fuhs, Allen E.
Date of Issue
1974-06
Date
June 1974
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
Abstract
NASA has recently published data on the effects of temperature and pressure distortion on the stability of axial-flow compressors. Theoretical predictions of compressor instability based on vorticity do not explain the observed compressor stability of the NASA tests. Description of distorted flow by vorticity is extended by a simplified model which incorporates vortex sheets and influence coefficients. To determine the upstream influence of the compressor on flow field distortion, a model using parallel compressor theory, experimental data from NASA, and a pressure ration equation derived by Hill and Peterson is formulated. The model correctly predicts compressor blade loading calculated by Carta. This new model accounts for upstream effects of the compressor and shows that the vorticity model by itself is incomplete. Incorporation of the new model into a distortion based index based on radial vorticity and total pressure change is proposed and discussed.
Type
Thesis
Description
Series/Report No
Department
Department of Aeronautics
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Funding
Format
Citation
Distribution Statement
Approved for public release; distribution is unlimited.
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.