Performance Limits of Axial Compressor Stages
Author(s)
Hall, David Kenneth
Greitzer, Edward M
Tan, Choon S
Date Issued
June 2012
Journal
Volume 8: Turbomachinery, Parts A, B, and C
Publisher
ASME International
Citation
Hall, D. K., E. M. Greitzer, and C. S. Tan. “Performance Limits of Axial Compressor Stages.” Volume 8: Turbomachinery, Parts A, B, and C (June 11, 2012).
Version
Final published version
Abstract
This paper presents a framework for estimating the upper limit of compressor stage efficiency. Using a compressor stage model with a representative design velocity distribution with turbulent boundary layers, losses are calculated as the sum of selected local irreversibilities, rather than from correlations based on data from existing machines. By considering only losses that cannot be eliminated and optimizing stage design variables for minimum loss, an upper bound on stage efficiency can be determined as a function of a small number of stage design parameters. The impact of the stage analysis results are evaluated in the context of gas turbine cycle performance. The implication from the results of the stage level and cycle analyses is that compressor efficiency improvements that result in substantial increases in cycle thermal efficiency are still to be realized.
MIT Department
MIT-SUTD Collaboration
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
Terms of Use
Article is made available in accordance with the publisher's policy and may be subject to US copyright law. Please refer to the publisher's site for terms of use.
Persistent DSpace Link
DOI of Published Version
https://doi.org/10.1115/GT2012-69709
