Rotating Stall Suppression Using Oscillatory Blowing Actuation on Blades

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.

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Document Details

Document Type
Technical Report
Publication Date
Jun 30, 2010
Accession Number
ADA547457

Entities

People

  • Othon K. Rediniotis
  • Paul G. A. Cizmas

Organizations

  • Texas Engineering Experiment Station

Tags

Communities of Interest

  • Energy and Power Technologies
  • Space

DTIC Thesaurus Topics

  • Boundary Layer
  • Compressors
  • Computational Fluid Dynamics
  • Computational Science
  • Control Systems
  • Differential Equations
  • Engineering
  • Fabrication
  • Flow Rate
  • Fluid Dynamics
  • Guide Vanes
  • Inlet Guide Vanes
  • Manufacturing
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Turbomachinery

Readers

  • Aerodynamics.
  • Aerodynamics/Aeronautics.
  • Aerospace Engineering