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dc.contributor.advisorEdward M. Greitzer.en_US
dc.contributor.authorAubry, Anne-Raphaëlleen_US
dc.contributor.otherMassachusetts Institute of Technology. Dept. of Aeronautics and Astronautics.en_US
dc.date.accessioned2013-01-07T21:19:50Z
dc.date.available2013-01-07T21:19:50Z
dc.date.copyright2012en_US
dc.date.issued2012en_US
dc.identifier.urihttp://hdl.handle.net/1721.1/76091
dc.descriptionThesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2012.en_US
dc.descriptionCataloged from PDF version of thesis.en_US
dc.descriptionIncludes bibliographical references (p. 61-63).en_US
dc.description.abstractThis thesis presents concepts for improving the performance of return channels in multi-stage centrifugal compressors. Geometries have been developed to reduce both separation and viscous losses. A number of different features with potential to reduce separation have also been investigated. The final proposed geometry uses a vaneless diffuser which narrows on the shroud side at the beginning of the 180' bend, an axially extended 1800 bend with increasing radius of curvature, and return channel vane leading edge radial position at an increased radius compared to the baseline. Three-dimensional calculations showed a 9% loss reduction compared to previous work [1], with a cumulative loss reduction of 19% compared to a baseline geometry. The geometry developed was based on specified inlet conditions. To examine the potential for increased performance if this constraint was removed, a return channel geometry was also defined that incorporated the same features but allowed modified inlet conditions, specifically radial inlet flow. The design of the impeller required for this new inlet flow was not considered. An overall loss reduction of 23% compared to baseline was found from the calculations. Modification of the impeller geometry is thus proposed as future work.en_US
dc.description.statementofresponsibilityby Anne-Raphaëlle Aubry.en_US
dc.format.extent63 p.en_US
dc.language.isoengen_US
dc.publisherMassachusetts Institute of Technologyen_US
dc.rightsM.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.urihttp://dspace.mit.edu/handle/1721.1/7582en_US
dc.subjectAeronautics and Astronautics.en_US
dc.titleReturn channel loss reduction in multi-stage centrifugal compressorsen_US
dc.typeThesisen_US
dc.description.degreeS.M.en_US
dc.contributor.departmentMassachusetts Institute of Technology. Department of Aeronautics and Astronautics
dc.identifier.oclc820261745en_US


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