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dc.contributor.advisorVavra, M. H.
dc.contributor.authorMarshall, Bruce Cameron
dc.dateSeptember 1967
dc.date.accessioned2012-08-29T23:30:52Z
dc.date.available2012-08-29T23:30:52Z
dc.date.issued1967
dc.identifier.urihttp://hdl.handle.net/10945/12064
dc.descriptionApproved for public release, distribution is unlimiteden_US
dc.description.abstractA mean streamline analysis of the effect of stator blade orientation on the performance of an axial flow compressor was performed by means of a computer program. Measurement were made on a 3-stage axial flow compressor at the Naval Postgraduate School at six stator stagger angles between 23.8 degrees and 44.3 degrees for a fixed orientation of the rotor blades. Maximum efficiency and pressure ratio were measured at a stator stagger angle of 31.8 degrees. Results at other blade settings showed that by varying stator stagger angle with flow rate optimum efficiencies and pressure rations can be achieved over a wide range of operating conditions. The result of this analysis were compared with the measured results. Suggestions are made for improving the manner of adapting cascade test data to performance predictions. By applying a non-dimensional deflection coefficient it could be shown that minimum work input corresponded to maximum efficiency. The test compressor has a tip diameter of 36 in. and a hub/tip ratio of 0.6. The blading tested is of the free-vortex type with a design degree of reaction of 0.5. Tip speed was about 185 ft/sec.en_US
dc.description.urihttp://www.archive.org/details/effectofstatorbl00mars
dc.language.isoen_US
dc.publisherMonterey, California. U.S. Naval Postgraduate Schoolen_US
dc.rightsThis publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. As such, it is in the public domain, and under the provisions of Title 17, United States Code, Section 105, may not be copyrighted.en_US
dc.subject.lcshAeronauticsen_US
dc.titleEffect of stator blade orientation on the performance of an axial flow compressoren_US
dc.typeThesisen_US
dc.contributor.corporateNaval Postgraduate School
dc.contributor.departmentDepartment of Aeronautics
dc.subject.authorCompressoren_US
dc.subject.authorCompressor performanceen_US
dc.subject.authorAxial flowen_US
dc.subject.authorVariable statoren_US
dc.subject.authorStator blade orientationen_US
dc.description.serviceLieutenant, United States Navyen_US
etd.thesisdegree.nameDegree of Aeronautical Engineeren_US
etd.thesisdegree.levelProfessional Degreeen_US
etd.thesisdegree.disciplineAeronautical Engineeringen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US


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