Impeller loss reduction in multi-stage centrifugal compressors
Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2015.
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| Other Authors: | |
| Format: | Thesis |
| Language: | eng |
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Massachusetts Institute of Technology
2015
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| Online Access: | http://hdl.handle.net/1721.1/97364 |
| _version_ | 1811084473667682304 |
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| author | Barile, Kristina (Kristina Marie) |
| author2 | Edward M. Greitzer. |
| author_facet | Edward M. Greitzer. Barile, Kristina (Kristina Marie) |
| author_sort | Barile, Kristina (Kristina Marie) |
| collection | MIT |
| description | Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2015. |
| first_indexed | 2024-09-23T12:51:21Z |
| format | Thesis |
| id | mit-1721.1/97364 |
| institution | Massachusetts Institute of Technology |
| language | eng |
| last_indexed | 2024-09-23T12:51:21Z |
| publishDate | 2015 |
| publisher | Massachusetts Institute of Technology |
| record_format | dspace |
| spelling | mit-1721.1/973642019-04-12T09:59:10Z Impeller loss reduction in multi-stage centrifugal compressors Barile, Kristina (Kristina Marie) Edward M. Greitzer. Massachusetts Institute of Technology. Department of Aeronautics and Astronautics. Massachusetts Institute of Technology. Department of Aeronautics and Astronautics. Aeronautics and Astronautics. 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). 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. by Kristina Barile. S.M. 2015-06-10T19:14:01Z 2015-06-10T19:14:01Z 2015 2015 Thesis http://hdl.handle.net/1721.1/97364 910635603 eng 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. http://dspace.mit.edu/handle/1721.1/7582 75 pages application/pdf Massachusetts Institute of Technology |
| spellingShingle | Aeronautics and Astronautics. Barile, Kristina (Kristina Marie) Impeller loss reduction in multi-stage centrifugal compressors |
| title | Impeller loss reduction in multi-stage centrifugal compressors |
| title_full | Impeller loss reduction in multi-stage centrifugal compressors |
| title_fullStr | Impeller loss reduction in multi-stage centrifugal compressors |
| title_full_unstemmed | Impeller loss reduction in multi-stage centrifugal compressors |
| title_short | Impeller loss reduction in multi-stage centrifugal compressors |
| title_sort | impeller loss reduction in multi stage centrifugal compressors |
| topic | Aeronautics and Astronautics. |
| url | http://hdl.handle.net/1721.1/97364 |
| work_keys_str_mv | AT barilekristinakristinamarie impellerlossreductioninmultistagecentrifugalcompressors |