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Control Design for an Advanced Geared Turbofan EngineThis paper describes the design process for the control system of an advanced geared turbofan engine. This process is applied to a simulation that is representative of a 30,000 pound-force thrust class concept engine with two main spools, ultra-high bypass ratio, and a variable area fan nozzle. Control system requirements constrain the non-linear engine model as it operates throughout its flight envelope of sea level to 40,000 feet and from 0 to 0.8 Mach. The purpose of this paper is to review the engine control design process for an advanced turbofan engine configuration. The control architecture selected for this project was developed from literature and reflects a configuration that utilizes a proportional integral controller with sets of limiters that enable the engine to operate safely throughout its flight envelope. Simulation results show the overall system meets performance requirements without exceeding operational limits.
Document ID
Document Type
Chapman, Jeffryes W.
(Vantage Partners, LLC Cleveland, OH, United States)
Litt, Jonathan S.
(NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
November 7, 2017
Publication Date
July 10, 2017
Subject Category
Aircraft Propulsion And Power
Aircraft Design, Testing And Performance
Report/Patent Number
Meeting Information
Meeting: AIAA Joint Propulsion Conference 2017
Location: Atlanta, GA
Country: United States
Start Date: July 10, 2017
End Date: July 12, 2017
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 109492.
Distribution Limits
Public Use Permitted.
system modeling
gas path dynamics
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