Aerodynamic Performance of a Flow Controlled Compressor Stator Using an Imbedded Ejector Pump

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dc.contributor.authorCarter, Casey Josephen
dc.contributor.committeechairNg, Wing Faien
dc.contributor.committeememberDancey, Clinton L.en
dc.contributor.committeememberBurdisso, Ricardo A.en
dc.contributor.departmentMechanical Engineeringen
dc.date.accessioned2014-03-14T20:32:02Zen
dc.date.adate2001-02-26en
dc.date.available2014-03-14T20:32:02Zen
dc.date.issued2001-02-09en
dc.date.rdate2002-02-26en
dc.date.sdate2001-02-21en
dc.description.abstractA high-turning compressor stator with a unique flow control design was developed and tested. Both boundary layer suction and trailing edge blowing developed from a single supplied motive pressure source are employed on the stator. Massflow removed through boundary layer suction is added to the motive massflow, and the resulting combined flow is used for trailing edge blowing to reduce the total pressure deficit generated by the stator wake. The effectiveness of the flow control design was investigated experimentally by measuring the reduction in the total pressure loss coefficient. The experiment was conducted in a linear transonic blowdown cascade wind tunnel. The inlet Mach number for all tests was 0.79, with a Reynolds number based on stator chordlength of 2,000,000. A range of inlet cascade angles was tested to identify the useful range of the flow control design. The effect of different supply massflows represented as a percentage of the passage throughflow was also documented. Significant reductions in the total pressure loss coefficient were accomplished with flow control at low cascade angles. A maximum reduction of 65% in the baseline (no flow control) loss coefficient was achieved by using a motive massflow of 1.6% of the passage throughflow, at cascade angle of 0°. The corresponding suction and blowing massflow ratio was approximately 1:3.6. Cascade angle results near 0° showed significant reductions in the loss coefficient, while increases in the cascade angle diminished the effects of flow control. Considerable suction side separation and the presence of a leading edge shock are noticeable as the cascade angle is increased, and contribute to the losses across the stator surface. Also identified was the estimated increase in wake turning due to flow control of up to 4.5°.en
dc.description.degreeMaster of Scienceen
dc.identifier.otheretd-02212001-093323en
dc.identifier.sourceurlhttp://scholar.lib.vt.edu/theses/available/etd-02212001-093323/en
dc.identifier.urihttp://hdl.handle.net/10919/31297en
dc.publisherVirginia Techen
dc.relation.haspartCasey_Carters_MS_Thesis.pdfen
dc.rightsIn Copyrighten
dc.rights.urihttp://rightsstatements.org/vocab/InC/1.0/en
dc.subjectFlow Controlen
dc.subjectCompressor Cascadeen
dc.subjectTrailing Edge Blowingen
dc.subjectAerodynamic Lossen
dc.subjectBoundary Layer Suctionen
dc.titleAerodynamic Performance of a Flow Controlled Compressor Stator Using an Imbedded Ejector Pumpen
dc.typeThesisen
thesis.degree.disciplineMechanical Engineeringen
thesis.degree.grantorVirginia Polytechnic Institute and State Universityen
thesis.degree.levelmastersen
thesis.degree.nameMaster of Scienceen

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