Characterization of performance-limiting flow mechanisms in a centrifugal compressor stage
Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2017.
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| Format: | Thesis |
| Language: | eng |
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Massachusetts Institute of Technology
2017
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| Online Access: | http://hdl.handle.net/1721.1/108928 |
| _version_ | 1811076104874622976 |
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| author | Erickson, David W., S.M. Massachusetts Institute of Technology |
| author2 | Choon S. Tan and Michael Macrorie. |
| author_facet | Choon S. Tan and Michael Macrorie. Erickson, David W., S.M. Massachusetts Institute of Technology |
| author_sort | Erickson, David W., S.M. Massachusetts Institute of Technology |
| collection | MIT |
| description | Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2017. |
| first_indexed | 2024-09-23T10:16:12Z |
| format | Thesis |
| id | mit-1721.1/108928 |
| institution | Massachusetts Institute of Technology |
| language | eng |
| last_indexed | 2024-09-23T10:16:12Z |
| publishDate | 2017 |
| publisher | Massachusetts Institute of Technology |
| record_format | dspace |
| spelling | mit-1721.1/1089282019-04-11T06:40:43Z Characterization of performance-limiting flow mechanisms in a centrifugal compressor stage Erickson, David W., S.M. Massachusetts Institute of Technology Choon S. Tan and Michael Macrorie. 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, 2017. Cataloged from PDF version of thesis. Includes bibliographical references (pages 269-270). This research characterizes the performance of a centrifugal compressor stage with a special focus on the pipe diffuser. Two diffuser configurations are studied, one of which is a truncated version of the other. Experimental data acquired on a research compressor stage is interrogated along with a set of well-designed Reynolds-Averaged Navier Stokes computations, complemented by reduced order flow modeling. The fundamental performance-limiting flow mechanisms in the diffuser are identified and used to physically relate important geometry features and operating conditions to the observed compressor pressure rise, efficiency, and operability characteristics. Despite large differences in their geometry, the two diffuser configurations exhibit similar pressure recovery characteristics due to differences in exit nonuniformity and flow angle which result in similar effective area ratios. Variations in the diffuser pressure recovery coefficient with operating point are found to be most influenced by the diffuser inlet flow angle, and secondly by the inlet Mach number. The diffuser inlet flow angle has the primary effect of setting the diffuser inlet one-dimensional area ratio, increasing diffusion at high flow angles. In addition, the diffuser incidence angle influences the formation of counter-rotating vortex pairs that persist throughout the diffuser passage. Using a two-dimensional integral boundary layer model that is modified to accommodate three-dimensional effects as source terms, these secondary flows are shown to detrimentally impact the diffuser pressure rise capability by accumulating high loss flow along the diffuser wall near the plane of symmetry between the vortices. This contributes to the extent and location of a large diffuser passage separation, especially for the baseline diffuser. The impact of the vortices on the boundary layer growth rate is shown to scale inversely with diffuser aspect ratio. The major performance difference between the two diffuser configurations is that the truncated diffuser configuration experiences enhanced stall margin over the baseline diffuser at the design speed. These differences are traced to reduced secondary flows influence and thus reduced separation extent for the higher aspect ratio truncated diffuser. It is hypothesized that the onset of stall for the baseline diffuser configuration is initiated by the transition of the vortex location and corresponding passage separation between diffuser pressure and suction sides with increasing cusp incidence. Conversely, because the extent of the passage separation in the truncated diffuser is diminished due to the higher aspect ratio, the switch in separation side does not immediately initiate instability. The fact that secondary flows have a large influence on diffuser pressure rise capability and compressor stability is counter to conventional preliminary diffuser design approaches which neglect such 3D effects. The findings of this research may therefore be considered during preliminary design optimization to produce better-performing diffuser designs. by David W. Erickson. S.M. 2017-05-11T19:56:13Z 2017-05-11T19:56:13Z 2017 2017 Thesis http://hdl.handle.net/1721.1/108928 986241884 eng MIT theses are protected by copyright. They may be viewed, downloaded, or printed from this source but further reproduction or distribution in any format is prohibited without written permission. http://dspace.mit.edu/handle/1721.1/7582 270 pages application/pdf Massachusetts Institute of Technology |
| spellingShingle | Aeronautics and Astronautics. Erickson, David W., S.M. Massachusetts Institute of Technology Characterization of performance-limiting flow mechanisms in a centrifugal compressor stage |
| title | Characterization of performance-limiting flow mechanisms in a centrifugal compressor stage |
| title_full | Characterization of performance-limiting flow mechanisms in a centrifugal compressor stage |
| title_fullStr | Characterization of performance-limiting flow mechanisms in a centrifugal compressor stage |
| title_full_unstemmed | Characterization of performance-limiting flow mechanisms in a centrifugal compressor stage |
| title_short | Characterization of performance-limiting flow mechanisms in a centrifugal compressor stage |
| title_sort | characterization of performance limiting flow mechanisms in a centrifugal compressor stage |
| topic | Aeronautics and Astronautics. |
| url | http://hdl.handle.net/1721.1/108928 |
| work_keys_str_mv | AT ericksondavidwsmmassachusettsinstituteoftechnology characterizationofperformancelimitingflowmechanismsinacentrifugalcompressorstage |