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Intelligent Engine Systems: Adaptive ControlWe have studied the application of the baseline Model Predictive Control (MPC) algorithm to the control of main fuel flow rate (WF36), variable bleed valve (AE24) and variable stator vane (STP25) control of a simulated high-bypass turbofan engine. Using reference trajectories for thrust and turbine inlet temperature (T41) generated by a simulated new engine, we have examined MPC for tracking these two reference outputs while controlling a deteriorated engine. We have examined the results of MPC control for six different transients: two idle-to-takeoff transients at sea level static (SLS) conditions, one takeoff-to-idle transient at SLS, a Bode power command and reverse Bode power command at 20,000 ft/Mach 0.5, and a reverse Bode transient at 35,000 ft/Mach 0.84. For all cases, our primary focus was on the computational effort required by MPC for varying MPC update rates, control horizons, and prediction horizons. We have also considered the effects of these MPC parameters on the performance of the control, with special emphasis on the thrust tracking error, the peak T41, and the sizes of violations of the constraints on the problem, primarily the booster stall margin limit, which for most cases is the lone constraint that is violated with any frequency.
Document ID
20080025995
Acquisition Source
Glenn Research Center
Document Type
Contractor Report (CR)
Authors
Gibson, Nathan (General Electric Aircraft Engines Cincinnati, OH, United States)
Date Acquired
August 24, 2013
Publication Date
June 1, 2008
Subject Category
Aeronautics (General)
Report/Patent Number
E-16499
NASA/CR-2008-215240
Funding Number(s)
CONTRACT_GRANT: NAS3-01135
WBS: WBS 984754.02.07.03.11.03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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