Rotating Stall Suppression Using Oscillatory Blowing Actuation on Blades

摘要

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.