compressor control
DESCRIPTION
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 (lb m ). Portable Real-Time Computer. Control Computer. - PowerPoint PPT PresentationTRANSCRIPT
University Research Engineering Technology Institute (URETI) on
Aeropropulsion & Power Technology (UAPT)
Compressor Control James Armor, Manuj Dhingra, Joseph Gillman, Vishwas Iyengar
Yi Liu, Yedidia Neumeier, J.V.R Prasad, L. SankarSchool of Aerospace EngineeringGeorgia Institute of Technology
1
1.1
1.2
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1.6
1.7
1.8
0 20 40 60 80 100 120
Nondimensionalized Mass flow Rate (% design value)
To
tal
Pre
ss
ure
Ra
tio
30% RPM
50% RPM
70% RPM
80% RPM
100% RPM
100% RPM Measurement
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
Rotor 67 Performance Map
M∞ = 0.2, T0 = 5º, circulation control jet Mj= 0.4
(a) No jet (b) Leading edge jet
Y X
ZFrame 001 13 Oct 2003 uvwFrame 001 13 Oct 2003 uvw
XY
ZFrame 001 13 Oct 2003 uvwFrame 001 13 Oct 2003 uvw
Effects of Circulation Control on leading edge of a nacelle
M∞ = 0.2, T0 = 0º, circulation control jet Mtrail= 0.4
(a) No jet (b) Trailing edge jet
Y X
ZFrame 001 13 Oct 2003 uvwFrame 001 13 Oct 2003 uvw
Y X
ZFrame 001 13 Oct 2003 uvwFrame 001 13 Oct 2003 uvw
Effects of Circulation Control on trailing edge region of a nacelle
Unblown Case Streamlines for Blown Case
Comparison between no circulation control and trailing edge blowing circulation control for a fixed wing
Flow Condition where circulation control was tested
Local separated flow due to high blade loading
Design Condition; 33.25 kg/sec Off-Design Condition; 29 kg/sec
Effects of Circulation Control Jet
c=0.0 c=0.11
Smaller region of flow reversal
Large reversed flow region
(a) (b)
Effect of Circulation Control on Flow Turningc=0.0 C=0.1
Velocity field in the blade fixed coordinate system at 10%R
Plenum Exhaust Duct Compressor (fan)KulitePressuresensor
Inlet
Control Computer
Portable Real-Time Computer
Pressure Sensor
Throttle Actuator
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 turningApplied our approach to a multi-stage compressor configuration
Surge
Demonstration of Active Stall control on the GT-Axial Facility
Controller overrides commanded throttle
Precursors Observed
Pressure Side
Suction Side
Away From Stall
Near Stall
Shaft Cycle
Co
rrel
atio
n
Mea
sure
Co
mp
ress
or
RP
M(u
nkn
ow
n u
nit
s)P
len
um
Pre
ssu
re(u
nkn
ow
n u
nit
s)
Stall
Advance warning
Engine Tests: Advance Stall Warning during transients
CFD Analysis of Compressor Performance
CFD Analysis of Nacelle and Center Bodies
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
Georgia Tech Axial Compressor RigStall Precursor Analysis
Mass Flow (lbm)
Pre
ssu
re R
atio
Open Loop
Mass Flow (lbm)
Pre
ssu
re R
atio
Closed Loop
Compressor Active Stall Control
Circulation Control Aerodynamics
Angle of Attack 0 degrees, Integral Flap at 30 degrees
0
1
2
3
4
5
0 0.05 0.1 0.15 0.2 0.25 0.3 0.35 0.4
C
Cl
Cl, Measured
Cl, Computed
Georgia Institute of TechnologyAtlanta, GeorgiaFounded 1885
Numerical Simulation Studies of Active Stall Control
Numerical Study of Circulation Control