An experimental investigation of a low Reynolds number, high Mach number centrifugal compressor
Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1998.
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| Format: | Thesis |
| Language: | eng |
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Massachusetts Institute of Technology
2005
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| Online Access: | http://hdl.handle.net/1721.1/9665 |
| _version_ | 1811082764715294720 |
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| author | Shirley, Gregory B. (Gregory Brenton), 1975- |
| author2 | Alan H. Epstein. |
| author_facet | Alan H. Epstein. Shirley, Gregory B. (Gregory Brenton), 1975- |
| author_sort | Shirley, Gregory B. (Gregory Brenton), 1975- |
| collection | MIT |
| description | Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1998. |
| first_indexed | 2024-09-23T12:08:38Z |
| format | Thesis |
| id | mit-1721.1/9665 |
| institution | Massachusetts Institute of Technology |
| language | eng |
| last_indexed | 2024-09-23T12:08:38Z |
| publishDate | 2005 |
| publisher | Massachusetts Institute of Technology |
| record_format | dspace |
| spelling | mit-1721.1/96652019-04-10T13:16:01Z An experimental investigation of a low Reynolds number, high Mach number centrifugal compressor Shirley, Gregory B. (Gregory Brenton), 1975- Alan H. Epstein. Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics Aeronautics and Astronautics Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1998. Includes bibliographical references (p. 119-120). Experiments were performed on a super-scale test facility to study the performance of very small centrifugal compressors suitable for microfabrication. ThE test facility was 75 times larger than the full-scale device and operated under 17/5 atmospheric pressure conditions to correctly match the Reynolds number, which is about 20,000. The impeller tip speed of the test facility matched those in the design full-scale device to capture the effects of compressibility. Two compressor geometries were tested, one with and one without diffuser vanes; the same impeller was used in both cases. For each of the diffuser designs, speed lines were determined at impeller tip speeds of 400 mis, corresponding to 100% of the design value, and 170 mis, corresponding to 42% of design. Detailed measurements were made at a single operating point on each of the speedlines. The test results show that the total-to-static pressure ratios developed by the facility are in agreement with CFO prediction. The measured mass flow rates are between the values predicted by 2-D and 3-D CFO. The performance of the vaned diffuser (Cp=0.48) is superior to that of the vaneless diffuser (Cp=0.24) in recovering the dynamic pressure of air exiting the impeller. The impeller isentropic efficiencies are about 0.48 and 0.27 for 100% and 42% design impeller speeds, respectively. These values are substantially lower than the predictions of CFO. The difference is thought to be due in part to the interaction of the flow in the impeller with the impeller casing, and to the effects of inlet separation. This study confirms computational predictions for pressure rise, and is consistent with compuational predictions of mass flow rate. However, the measured efficiency is lower than CFD predictions. Additional testing is required to determine the sources of loss in the impeller. by Gregory B. Shirley. S.M. 2005-08-19T19:18:08Z 2005-08-19T19:18:08Z 1998 1998 Thesis http://hdl.handle.net/1721.1/9665 42461339 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 120 p. 7755241 bytes 7755002 bytes application/pdf application/pdf application/pdf Massachusetts Institute of Technology |
| spellingShingle | Aeronautics and Astronautics Shirley, Gregory B. (Gregory Brenton), 1975- An experimental investigation of a low Reynolds number, high Mach number centrifugal compressor |
| title | An experimental investigation of a low Reynolds number, high Mach number centrifugal compressor |
| title_full | An experimental investigation of a low Reynolds number, high Mach number centrifugal compressor |
| title_fullStr | An experimental investigation of a low Reynolds number, high Mach number centrifugal compressor |
| title_full_unstemmed | An experimental investigation of a low Reynolds number, high Mach number centrifugal compressor |
| title_short | An experimental investigation of a low Reynolds number, high Mach number centrifugal compressor |
| title_sort | experimental investigation of a low reynolds number high mach number centrifugal compressor |
| topic | Aeronautics and Astronautics |
| url | http://hdl.handle.net/1721.1/9665 |
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