Role of tip clearance flow on axial compressor stability
Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, February 2002.
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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/1721.1/8104 |
| _version_ | 1826209807081668608 |
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| author | Vo, Huu Duc, 1971- |
| author2 | Choon S. Tan and Edward M. Greitzer. |
| author_facet | Choon S. Tan and Edward M. Greitzer. Vo, Huu Duc, 1971- |
| author_sort | Vo, Huu Duc, 1971- |
| collection | MIT |
| description | Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, February 2002. |
| first_indexed | 2024-09-23T14:31:41Z |
| format | Thesis |
| id | mit-1721.1/8104 |
| institution | Massachusetts Institute of Technology |
| language | eng |
| last_indexed | 2024-09-23T14:31:41Z |
| publishDate | 2005 |
| publisher | Massachusetts Institute of Technology |
| record_format | dspace |
| spelling | mit-1721.1/81042019-04-12T15:24:36Z Role of tip clearance flow on axial compressor stability Vo, Huu Duc, 1971- 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 (Ph. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, February 2002. Includes bibliographical references (p. 75-78). An examination of the fluid dynamic phenomena that link tip clearance flow to the formation of short length-scale (spike) rotating stall disturbances has been carried out. It is found that the onset of growth in tip clearance blockage characterizes the lowest flow coefficient for which a steady blade passage solution exists. It is also found that this condition leads to the formation of spike disturbances. A scenario and criteria for this tip clearance blockage behavior are proposed based on trailing edge backflow and leading edge spillage to the adjacent blade passage. Both are associated with tip clearance flow and occur below the blade tip. Trailing edge backflow involves tip clearance fluid from adjacent blade passages. The leading edge spillage consists of tip clearance fluid from the local blade passage. These two criteria explain the observed length-scale of spike disturbances. This scenario is consistent with several experimental observations on axial compressor stall inception. The implications of these results on the role of single blade passage computations in stall prediction and on the effectiveness of techniques used to delay stall are also discussed. by Huu Duc Vo. Ph.D. 2005-08-24T20:21:53Z 2005-08-24T20:21:53Z 2001 2002 Thesis http://hdl.handle.net/1721.1/8104 51284048 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 95 p. 6594481 bytes 6594237 bytes application/pdf application/pdf application/pdf Massachusetts Institute of Technology |
| spellingShingle | Aeronautics and Astronautics. Vo, Huu Duc, 1971- Role of tip clearance flow on axial compressor stability |
| title | Role of tip clearance flow on axial compressor stability |
| title_full | Role of tip clearance flow on axial compressor stability |
| title_fullStr | Role of tip clearance flow on axial compressor stability |
| title_full_unstemmed | Role of tip clearance flow on axial compressor stability |
| title_short | Role of tip clearance flow on axial compressor stability |
| title_sort | role of tip clearance flow on axial compressor stability |
| topic | Aeronautics and Astronautics. |
| url | http://hdl.handle.net/1721.1/8104 |
| work_keys_str_mv | AT vohuuduc1971 roleoftipclearanceflowonaxialcompressorstability |