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dc.contributor.authorHale, Alan A.en_US
dc.date.accessioned2014-03-14T21:12:34Z
dc.date.available2014-03-14T21:12:34Z
dc.date.issued1996-12-15en_US
dc.identifier.otheretd-06062008-154548en_US
dc.identifier.urihttp://hdl.handle.net/10919/38081
dc.description.abstractModem high-performance military aircraft are subjected to rapid flight maneuvers which place great operational demands on their compression system by producing highly distorted flow to the compressor. Inlet distortion generally reduces the engine compressor stability margin and may induce compressor surge at high rotational speeds, or rotating stall at lower rotational speeds. Therefore, a computational fluid dynamics (CFD) based compressor simulation would be very useful in the design, test, and analysis process since it gives additional information with inexpensive modifications.

A new CFD simulation called the Turbine Engine Analysis Compressor Code (TEACC) was designed to meet these requirements. This code solves the compressible 3D Euler equations modified to include turbomachinery source terms which simulates the effect of the compressor blades. The source terms are calculated for each blade row by the application of a streamline curvature code. A methodology was developed for calculating turbomachinery source terms and distributing them axially, radially, and circumferentially while maintaining a sensitivity to strong inlet distortion.

TEACC was compared with experimental data from NASA Rotor 1 B, a transonic rotor. Experimental data from Rotor 1 B were available for comparison with TEACC results for a clean inlet and for an inlet distortion produced by a 90-degree, one-perrevolution screen. TEACC results compared very well with experimental data with a clean inlet. Comparison with experimental data with inlet distortion demonstrated TEACC's ability to characterize the compressor overall, and to accurately predict the magnitude and shape of exit total temperature and exit total pressure in the distorted region. TEACC calculated the overall character of exit total pressure and exit total temperature in the nondistorted region, identifying the location of the largest value just after the inlet distortion and the decrease in exit total values through the nondistorted region in the direction of rotation.

en_US
dc.format.mediumBTDen_US
dc.publisherVirginia Techen_US
dc.relation.haspartLD5655.V856_1996.H354.pdfen_US
dc.subjectdistortionen_US
dc.subjectcompressoren_US
dc.subjectthree-dimensionalen_US
dc.subjectsimulationen_US
dc.subject.lccLD5655.V856 1996.H354en_US
dc.titleA three-dimensional turbine engine analysis compressor code (TEACC) for steady-state inlet distortionen_US
dc.typeDissertationen_US
dc.contributor.departmentMechanical Engineeringen_US
dc.description.degreePh. D.en_US
thesis.degree.namePh. D.en_US
thesis.degree.leveldoctoralen_US
thesis.degree.grantorVirginia Polytechnic Institute and State Universityen_US
thesis.degree.disciplineMechanical Engineeringen_US
dc.contributor.committeechairO'Brien, Walter F. Jr.en_US
dc.contributor.committeememberMoore, Johnen_US
dc.contributor.committeememberDavis, Milton W. Jr.en_US
dc.contributor.committeememberNg, Faien_US
dc.contributor.committeememberWatson, Layne T.en_US
dc.identifier.sourceurlhttp://scholar.lib.vt.edu/theses/available/etd-06062008-154548/en_US
dc.date.sdate2008-06-06en_US
dc.date.rdate2008-06-06
dc.date.adate2008-06-06en_US


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