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dc.contributor.advisorHobson, Garth V.
dc.contributor.advisorGannon, Anthony J.
dc.contributor.authorDrayton, Scott
dc.dateSep-13
dc.date.accessioned2013-11-20T23:36:03Z
dc.date.available2013-11-20T23:36:03Z
dc.date.issued2013-09
dc.identifier.urihttp://hdl.handle.net/10945/37616
dc.description.abstractA new design procedure was developed and documented that uses commercial-off-the-shelf software (MATLAB, SolidWorks, and ANSYS-CFX) for the geometric rendering and analysis of a transonic axial compressor rotor with splitter blades. Predictive numerical simulations were conducted and experimental data were collected at the NPS TPL utilizing the Transonic Compressor Rig. This study advanced the understanding of splitter blade geometry, placement, and performance benefits. In particular, it was determined that moving the splitter blade forward in the passage between the main blades, which was a departure from the trends demonstrated in the few available previous transonic axial compressor splitter blade studies, increased the mass flow range with no loss in overall performance. With a large 0.91 mm (0.036 in) tip clearance, to preserve the integrity of the rotor, the experimentally measured peak total-to-total pressure ratio was 1.69 and the peak total-to-total isentropic efficiency was 72 percent at 100 percent design speed. Additionally, a higher than predicted 7.5 percent mass flow rate range was experimentally measured, which would make for easier engine control if this concept were to be included in an actual gas turbine engine.en_US
dc.description.urihttp://archive.org/details/designtestndeval1094537616
dc.publisherMonterey, California: 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. Copyright protection is not available for this work in the United States.en_US
dc.titleDesign, test, and evaluation of a transonic axial compressor rotor with splitter bladesen_US
dc.typeThesisen_US
dc.contributor.departmentMechanical and Aerospace Engineering (MAE)
dc.subject.authorTransonicen_US
dc.subject.authorAxial Compressoren_US
dc.subject.authorRotoren_US
dc.subject.authorSplittereden_US
dc.subject.authorSplitter Bladeen_US
dc.subject.authorDesign Toolen_US
dc.description.serviceCommander, United States Navyen_US
etd.thesisdegree.nameDoctor of Philosophy In Mechanical Engineeringen_US
etd.thesisdegree.levelDoctoralen_US
etd.thesisdegree.disciplineMechanical Engineeringen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US
dc.description.distributionstatementApproved for public release; distribution is unlimited.


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