Effect of circumferential groove casing treatment parameters on axial compressor flow range
Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2010.
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| Formaat: | Thesis |
| Taal: | eng |
| Gepubliceerd in: |
Massachusetts Institute of Technology
2010
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| Online toegang: | http://hdl.handle.net/1721.1/59675 |
| _version_ | 1826200820920614912 |
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| author | Hanley, Brian K. (Brian Kyle) |
| author2 | Choon S. Tan and Edward M. Greitzer. |
| author_facet | Choon S. Tan and Edward M. Greitzer. Hanley, Brian K. (Brian Kyle) |
| author_sort | Hanley, Brian K. (Brian Kyle) |
| collection | MIT |
| description | Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2010. |
| first_indexed | 2024-09-23T11:42:19Z |
| format | Thesis |
| id | mit-1721.1/59675 |
| institution | Massachusetts Institute of Technology |
| language | eng |
| last_indexed | 2024-09-23T11:42:19Z |
| publishDate | 2010 |
| publisher | Massachusetts Institute of Technology |
| record_format | dspace |
| spelling | mit-1721.1/596752019-04-15T00:27:25Z Effect of circumferential groove casing treatment parameters on axial compressor flow range Hanley, Brian K. (Brian Kyle) Choon S. Tan and Edward M. Greitzer. Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics. Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics. Aeronautics and Astronautics. Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2010. Cataloged from PDF version of thesis. Includes bibliographical references (p. 77). The impact on compressor flow range of circumferential casing grooves of varying groove depth, groove axial location, and groove axial extent is assessed against that of a smooth casing wall using computational experiments. The computed results show that maximum range improvement is obtained for a groove depth of approximately a tip clearance and of an axial width of approximately 0.175 axial chord (approximately the near stall tip clearance vortex core size for the smoothwall compressor examined). It was found that for a groove of specified depth and axial width there are two axial locations, one at approximately 0.15 axial chord and one at approximately 0.6 axial chord from the rotor blade leading edge, to position the groove for maximum flow range improvement; this result is in accord with recent experimental observations. In addition, a method of extracting body forces is used to show that the force is finite at the blade tip and non-vanishing in the tip clearance. by Brian K. Hanley. S.M. 2010-10-29T18:09:16Z 2010-10-29T18:09:16Z 2010 2010 Thesis http://hdl.handle.net/1721.1/59675 668214452 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 77 p. application/pdf Massachusetts Institute of Technology |
| spellingShingle | Aeronautics and Astronautics. Hanley, Brian K. (Brian Kyle) Effect of circumferential groove casing treatment parameters on axial compressor flow range |
| title | Effect of circumferential groove casing treatment parameters on axial compressor flow range |
| title_full | Effect of circumferential groove casing treatment parameters on axial compressor flow range |
| title_fullStr | Effect of circumferential groove casing treatment parameters on axial compressor flow range |
| title_full_unstemmed | Effect of circumferential groove casing treatment parameters on axial compressor flow range |
| title_short | Effect of circumferential groove casing treatment parameters on axial compressor flow range |
| title_sort | effect of circumferential groove casing treatment parameters on axial compressor flow range |
| topic | Aeronautics and Astronautics. |
| url | http://hdl.handle.net/1721.1/59675 |
| work_keys_str_mv | AT hanleybriankbriankyle effectofcircumferentialgroovecasingtreatmentparametersonaxialcompressorflowrange |