Impeller loss reduction in multi-stage centrifugal compressors
Name
910635603-MIT.pdf
Description
Full printable version
Size
11.56 MB
Format
Adobe PDF
Checksum (MD5)
8580600ebbc6dc7da3e41498ad5126d8
Author(s)
Barile, Kristina (Kristina Marie)
Advisor(s)
Edward M. Greitzer.
Date Issued
2015
Publisher
Massachusetts Institute of Technology
Abstract
Loss generation features for the first stage impeller in a multistage centrifugal compressor are examined using three-dimensional RANS computations. The calculations were carried out for a baseline configuration and for seven other impeller configurations, with the constraints of constant mass flow and constant work per unit mass flow. The computations showed an 8 percent reduction in loss, compared to the baseline, for a configuration that incorporated 60% of the total casing blade angle change in the front 20% chord. Twodimensional interactive boundary layer computations were carried out to demonstrate links between the loss variation and the changes in boundary layer behavior in the front 20% of the blade passage.
Description
Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2015.
Cataloged from PDF version of thesis.
Includes bibliographical references (pages 74-75).
Subjects
Aeronautics and Astronautics.
MIT Department
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
Terms of Use
M.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. See provided URL for inquiries about permission.
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