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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
20170008458
Acquisition Source
Glenn Research Center
Document Type
Presentation
Authors
Chapman, Jeffryes W.
(Vantage Partners, LLC Cleveland, OH, United States)
Litt, Jonathan
(NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
September 5, 2017
Publication Date
July 10, 2017
Subject Category
Aircraft Design, Testing And Performance
Aeronautics (General)
Report/Patent Number
GRC-E-DAA-TN44128
Meeting Information
Meeting: 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)
CONTRACT_GRANT: NNC12BA01B
WBS: WBS 109492.02.03.02.11.01
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
aerothermodynamics
gas path dynamics
system modeling
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