Compressor Control

1. Compressor Control Exhaust Duct Off-Design Condition; 29 kg/sec Compressor (fan) Design Condition; 33.25 kg/sec Plenum Kulite Pressure sensor Pressure Sensor Pressure Ratio Inlet Mass Flow (lbm) Portable Real-Time Computer Control Computer Local separated flow due to high blade loading Pressure Ratio Throttle Actuator Mass Flow (lbm) Circulation Control Aerodynamics Angle of Attack 0 degrees, Integral Flap at 30 degrees Comparison between no circulation control and trailing edge blowing circulation control for a fixed wing Demonstration of Active Stall control on the GT-Axial Facility Surge Pressure Side Open Loop Away From Stall Shaft Cycle Closed Loop Streamlines for Blown Case Unblown Case Suction Side Flow Condition where circulation control was tested Effects of Circulation Control on leading edge of a nacelle Near Stall (a) No jet (b) Leading edge jet Controller overrides commanded throttle Large reversed flow region Smaller region of flow reversal Engine Tests: Advance Stall Warning during transients cm=0.0 cm=0.11 Advance warning Effects of Circulation Control Jet M∞ = 0.2, DT0 = 5º, circulation control jet Mj= 0.4 Correlation Measure Effects of Circulation Control on trailing edge region of a nacelle (b) Trailing edge jet (a) No jet Compressor RPM (unknown units) Precursors Observed (a) (b) Stall cm=0.0 Cm=0.1 Plenum Pressure (unknown units) M∞ = 0.2, DT0 = 0º, circulation control jet Mtrail= 0.4 Velocity field in the blade fixed coordinate system at 10%R James Armor, Manuj Dhingra, Joseph Gillman, Vishwas Iyengar Yi Liu, Yedidia Neumeier, J.V.R Prasad, L. Sankar School of Aerospace Engineering Georgia Institute of Technology Jvr.prasad@ae.gatech.edu CFD Analysis of Compressor Performance Numerical Study of Circulation Control Compressor Active Stall Control Rotor 67 Performance Map Georgia Tech Axial Compressor Rig Stall Precursor Analysis • Completed validation of the analysis through a component map generation for Rotors 67 and 37. • Delivered the compressor analysis, with sample user input/output and sample grids, for adaptation to design methodologies • Improved turn-around time 4 to 6 fold by parallelizing the analysis on OpenMP systems using 8 CPUs Numerical Simulation Studies of Active Stall Control CFD Analysis of Nacelle and Center Bodies Effect of Circulation Control on Flow Turning • Completed a version of the analysis that can model flow through nacelles and center-bodies. The fan blades may be individually modeled, or represented as an actuator disk. • Delivered the nacelle analysis, with sample user input/output and sample grids, for adaptation to design methodologies • Implemented real-time auto-correlation algorithm on a portable system. • Integrated the auto-correlation based active stall avoidance scheme with a full engine controller. • Demonstrated active stall avoidance on a full engine during rapid transients. • Completed the evaluation of the recirculation and circulation control concepts as a means of increasing the blade loading, and for achieving flow turning • Applied our approach to a multi-stage compressor configuration