Accession Number : ADA547457


Title :   Rotating Stall Suppression Using Oscillatory Blowing Actuation on Blades


Descriptive Note : Final rept.


Corporate Author : TEXAS ENGINEERING EXPERIMENT STATION COLLEGE STATION


Personal Author(s) : Cizmas, Paul G ; Rediniotis, Othon K


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a547457.pdf


Report Date : 30 Jun 2010


Pagination or Media Count : 39


Abstract : Highly maneuverable aircraft require that the propulsion system (jet engine) operates during sudden accelerations and rapid changes in inlet conditions. Consequently, the compressor of the jet engine occasionally must operate at low flow rates and high angles of attack. The high-angle- of-attack low-flow regime of compressor operation is often plagued by rotating stall and surge. Rotating stall and surge cannot be tolerated during compression operation because: (1) they can be catastrophic to engine performance, (2) they cause rapid heating of the blades, and (3) they can induce severe mechanical stresses. Traditional methods for surge and separation control have included: (1) use of bleed-air off-take, (2) use of variable inlet guide vanes and variable inlet stator vanes, and (3) casing air injection upstream of the blade tip.


Descriptors :   *OSCILLATION , *BLADE TIPS , *AXIAL FLOW COMPRESSORS , *ROTOR BLADES , *PROPULSION SYSTEMS , ANGLE OF ATTACK , FLOW RATE , HEATING , STATORS , CATASTROPHIC CONDITIONS , ROTATION , ACTUATION , SUPPRESSION , GUIDE VANES , PERFORMANCE(ENGINEERING) , MANEUVERABILITY , MECHANICAL PROPERTIES , INLET GUIDE VANES , COMPRESSION , STRESSES


Subject Categories : Air Condition, Heating, Lighting & Ventilating
      Machinery and Tools
      Mechanics


Distribution Statement : APPROVED FOR PUBLIC RELEASE