Effect of struts on aeroacoustics of axisymmetric supersonic inlets

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dc.contributor.authorPande, Abhijiten
dc.contributor.departmentMechanical Engineeringen
dc.date.accessioned2014-03-14T21:41:37Zen
dc.date.adate2009-07-29en
dc.date.available2014-03-14T21:41:37Zen
dc.date.issued1994en
dc.date.rdate2009-07-29en
dc.date.sdate2009-07-29en
dc.description.abstractA study was conducted to determine the effect of strut position on the aerodynamic and acoustic performance of a supersonic inlet. The investigated inlet was a prototype 1/14 scale model of a mixed compression, axisymmetric supersonic inlet designed for the high speed civil transport aircraft. A 10.4 cm (4.1 in.) turbofan engine simulator was used in conjunction with the inlet to provide the typical noise signature of a high bypass turbofan engine. Two inlet configurations were investigated in this study. The first configuration was the standard inlet design where the struts are located immediately upstream of the fan. The new configuration has the struts located 3.3 chord length upstream of the fan. The purpose for relocating the strut position was to reduce the flow distortion and radiated noise level. The experiment was conducted at various fan operating conditions in order to simulate aircraft approach. The inlet was tested statically without simulating the inflight speed effects. Steady state measurements were made in order to evaluate the aerodynamic performance of the inlet. The aerodynamic results show that the movement of the struts to a new location allowed the strut wake to diffuse significantly before reaching the fan. This reduced the circumferential distortion parameter by a factor of 2.4, without affecting the pressure recovery of the inlet at a fan Abstract speed of 30,000 rpm (40 PNC). Acoustic measurements were taken in the far field in the 0°-110°sector from the inlet axis. The new configuration of the inlet showed an improved acoustic performance over the standard design. Relocating the struts upstream reduced the blade passing tone by an average of 8 dB (0°-110°) sector, and the overall sound pressure level was lowered by an average of 2.6 dB at a fan speed of 30,000 rpm (40 PNC).en
dc.description.degreeMaster of Scienceen
dc.format.extentxi, 87 leavesen
dc.format.mediumBTDen
dc.format.mimetypeapplication/pdfen
dc.identifier.otheretd-07292009-090449en
dc.identifier.sourceurlhttp://scholar.lib.vt.edu/theses/available/etd-07292009-090449/en
dc.identifier.urihttp://hdl.handle.net/10919/43999en
dc.language.isoenen
dc.publisherVirginia Techen
dc.relation.haspartLD5655.V855_1994.P363.pdfen
dc.relation.isformatofOCLC# 32290316en
dc.rightsIn Copyrighten
dc.rights.urihttp://rightsstatements.org/vocab/InC/1.0/en
dc.subject.lccLD5655.V855 1994.P363en
dc.subject.lcshAerodynamic noiseen
dc.subject.lcshAerodynamics, Supersonicen
dc.subject.lcshStruts (Engineering)en
dc.titleEffect of struts on aeroacoustics of axisymmetric supersonic inletsen
dc.typeThesisen
dc.type.dcmitypeTexten
thesis.degree.disciplineMechanical Engineeringen
thesis.degree.grantorVirginia Polytechnic Institute and State Universityen
thesis.degree.levelmastersen
thesis.degree.nameMaster of Scienceen

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