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Experimental studies in a supersonic through-flow fan blade cascade

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dc.contributor.authorChesnakas, Christopher J.en
dc.contributor.committeechairNg, Faien
dc.contributor.committeememberDancey, Clinton L.en
dc.contributor.committeememberO'Brien, Walter F. Jr.en
dc.contributor.committeememberRoe, Larry A.en
dc.contributor.committeememberSchetz, Joseph A.en
dc.contributor.departmentMechanical Engineeringen
dc.date.accessioned2014-03-14T21:20:55Zen
dc.date.adate2005-10-12en
dc.date.available2014-03-14T21:20:55Zen
dc.date.issued1991-05-06en
dc.date.rdate2005-10-12en
dc.date.sdate2005-10-12en
dc.description.abstractAn investigation has been performed of the flow in a supersonic through-flow fan blade cascade. The blade shapes are those of the baseline supersonic through-flow fan (STFF) under investigation at the NASA Lewis Research Center. Measurements were made at an inlet Mach number of 2.36 over a 15° range of incidence. Flowfield wave patterns were recorded using spark shadowgraph photography and steady-state instrumentation was used to measure blade surface pressure distributions and downstream total and static pressure distributions. A two-dimensional LDV system was used to map the downstream flowfield. From these measurements, the integrated loss coefficients are presented as a function of incidence angle along with analysis indicating the source of losses in the STFF cascade. The results are compared with calculations made using a two-dimensional, cell-centered, finite-volume, Navier-Stokes code with upwind options. Good general agreement is found at design conditions, with lesser agreement at off-design conditions. Analysis of the leading edge shock shows that the leading edge radius is a major source of losses in STFF blades. Losses from the leading edge bluntness are convected downstream into the blade wake, and are difficult to distinguish from viscous losses. Shock losses are estimated to account for 70% to 80% of the losses in the STFF cascade.en
dc.description.degreePh. D.en
dc.format.extentxiv, 143 leavesen
dc.format.mediumBTDen
dc.format.mimetypeapplication/pdfen
dc.identifier.otheretd-10122005-134450en
dc.identifier.sourceurlhttp://scholar.lib.vt.edu/theses/available/etd-10122005-134450/en
dc.identifier.urihttp://hdl.handle.net/10919/39790en
dc.language.isoenen
dc.publisherVirginia Techen
dc.relation.haspartLD5655.V856_1991.C547.pdfen
dc.relation.isformatofOCLC# 29179339en
dc.rightsIn Copyrighten
dc.rights.urihttp://rightsstatements.org/vocab/InC/1.0/en
dc.subject.lccLD5655.V856 1991.C547en
dc.subject.lcshAerodynamics, Supersonicen
dc.subject.lcshAirplanes -- Turbojet engines -- Bladesen
dc.subject.lcshCascades (Fluid dynamics)en
dc.titleExperimental studies in a supersonic through-flow fan blade cascadeen
dc.typeDissertationen
dc.type.dcmitypeTexten
thesis.degree.disciplineMechanical Engineeringen
thesis.degree.grantorVirginia Polytechnic Institute and State Universityen
thesis.degree.leveldoctoralen
thesis.degree.namePh. D.en

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