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dc.contributor.advisorHobson, Garth V.
dc.contributor.authorGreco, Philip Andrew
dc.dateSeptember 1995
dc.date.accessioned2012-07-31T19:54:35Z
dc.date.available2012-07-31T19:54:35Z
dc.date.issued1995-09
dc.identifier.urihttp://hdl.handle.net/10945/7566
dc.description.abstractThe redesign, data acquisition system installation, and software development for the cold-flow Turbine Test Rig is reported. The turbine tested was the Space Shuttle Main Engine High Pressure Fuel Turbopump first stage 'Alternate Turbopump Development' model designed and manufactured by Pratt & Whitney. The purpose of - this research was to establish a continuously operating, cdd-flow, turbine test facility which could be used for future laser-Doppler-velocimetry measurements in the tip leakage region of the turbine rotor blades. Also, to determine both the single and two stage turbine performance parameters, and to provide a test model for comparison with numerical simulations using a three-dimensional viscous flow code. A throttle valve was designed and installed at the turbine exit to control the pressure ratio in order to map the turbine performance. Data acquisition, reduction and display programs were developed using LabVIEW Visual Instrument software in order to collect, and process the data. The first-stage turbine exit velocity profile was measured using a cobra probe. Also, the first-stage turbine performance characteristics were determined. Flow-field characteristics of the first stage turbine were predicted using a three-dimensional viscous flow code.en_US
dc.description.urihttp://archive.org/details/turbineperforman109457566
dc.format.extent147 p.en_US
dc.language.isoen_US
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.titleTurbine performance mapping of the space-shuttle main engine high-pressure fuel turbopumpen_US
dc.typeThesisen_US
dc.contributor.departmentAeronautical Engineering
dc.description.serviceU.S. Navy (U.S.N.) author.en_US
etd.thesisdegree.nameM.S. in Aeronautical Engineeringen_US
etd.thesisdegree.levelMastersen_US
etd.thesisdegree.disciplineAeronautical Engineeringen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US
dc.description.distributionstatementApproved for public release; distribution is unlimited.


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