Show simple item record

dc.contributor.advisorChoon S. Tan.en_US
dc.contributor.authorVillanueva V., Alfonso D. (Villanueva Villarreal)en_US
dc.contributor.otherMassachusetts Institute of Technology. Dept. of Aeronautics and Astronautics.en_US
dc.date.accessioned2007-01-10T16:38:32Z
dc.date.available2007-01-10T16:38:32Z
dc.date.copyright2006en_US
dc.date.issued2006en_US
dc.identifier.urihttp://hdl.handle.net/1721.1/35559
dc.descriptionThesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2006.en_US
dc.descriptionIncludes bibliographical references (p. 99-100).en_US
dc.description.abstractThe unsteady three-dimensional flow field for two centrifugal compressors of nearly identical design (one with a marginally smaller impeller-diffuser gap) is interrogated to assess the difference in the time averaged performance and unsteady loading characteristics of the impeller blades. Computational calculations are conducted for three different operating points. Results show that the difference in the time-average performance of the two compressors is due to the change in the level of loss and blockage generated from a difference in the strength of the impeller-diffuser interaction between the two compressors. The unsteady component of loading on the impeller blade originates from pressure waves propagating with a phase difference on the suction and pressure surfaces of the blades. The frequency of the waves is set by the diffuser vanes passing frequency and the wavelength by the product of the diffuser vane passing period and the speed of the wave. It is demonstrated that the difference in static pressure from the pressure surface to the suction surface at the leading edge of the diffuser vanes sets the amplitude of unsteady loading on the blades of the impeller.en_US
dc.description.abstract(cont.) The level of pressure on both surfaces of the diffuser vane at the leading edge is determined by the value of the local angle of incidence. It is concluded that for a given diffuser design, changes in the impeller configuration or impeller-diffuser gap that result in a variation of the diffuser incidence will lead to a different unsteady loading distribution on the blades of the impeller.en_US
dc.description.statementofresponsibilityby Alfonso D. Villanueva V.en_US
dc.format.extent100 p.en_US
dc.format.extent4918064 bytes
dc.format.extent4922185 bytes
dc.format.mimetypeapplication/pdf
dc.format.mimetypeapplication/pdf
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/1721.1/7582
dc.subjectAeronautics and Astronautics.en_US
dc.titleCharacterization of the flow field response to vaneless space reduction in centrifugal compressorsen_US
dc.typeThesisen_US
dc.description.degreeS.M.en_US
dc.contributor.departmentMassachusetts Institute of Technology. Dept. of Aeronautics and Astronautics.en_US
dc.contributor.departmentMassachusetts Institute of Technology. Department of Aeronautics and Astronautics
dc.identifier.oclc73812047en_US


Files in this item

Thumbnail

This item appears in the following Collection(s)

Show simple item record