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Effect of circumferential groove casing treatment parameters on axial compressor flow range

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dc.contributor.advisor Choon S. Tan and Edward M. Greitzer. en_US
dc.contributor.author Hanley, Brian K. (Brian Kyle) en_US
dc.contributor.other Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics. en_US
dc.date.accessioned 2010-10-29T18:09:16Z
dc.date.available 2010-10-29T18:09:16Z
dc.date.copyright 2010 en_US
dc.date.issued 2010 en_US
dc.identifier.uri http://hdl.handle.net/1721.1/59675
dc.description Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2010. en_US
dc.description Cataloged from PDF version of thesis. en_US
dc.description Includes bibliographical references (p. 77). en_US
dc.description.abstract 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. en_US
dc.description.statementofresponsibility by Brian K. Hanley. en_US
dc.format.extent 77 p. en_US
dc.language.iso eng en_US
dc.publisher Massachusetts Institute of Technology en_US
dc.rights 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. en_US
dc.rights.uri http://dspace.mit.edu/handle/1721.1/7582 en_US
dc.subject Aeronautics and Astronautics. en_US
dc.title Effect of circumferential groove casing treatment parameters on axial compressor flow range en_US
dc.type Thesis en_US
dc.description.degree S.M. en_US
dc.contributor.department Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics. en_US
dc.identifier.oclc 668214452 en_US


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MIT-Mirage