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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 lbf 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 ft and from 0 to 0.8 Mach. The control architecture selected for this project was developed from literature and reflects a configuration that utilizes a proportional integral controller integrated 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 system operational limits.
Document ID
20170011210
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Chapman, Jeffryes W. (Vantage Partners, LLC Cleveland, OH, United States)
Litt, Jonathan S. (NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
November 22, 2017
Publication Date
November 1, 2017
Subject Category
Fluid Mechanics And Thermodynamics
Aircraft Propulsion And Power
Aeronautics (General)
Report/Patent Number
NASA/TM-2017-219569
AIAA Paper 2017-4820
E-19416
GRC-E-DAA-TN46240
Meeting Information
Meeting: AIAA Propulsion and Energy Forum
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)
CONTRACT_GRANT: NNC12BA01B
WBS: WBS 109492.02.03.02.11.01
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
gas path dynamics
aerothermodynamics
system modeling

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