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Thermal Modeling of an Advanced Geared Turbofan for Distributed Engine Control ApplicationReliability and life-expectancy of gas turbine engine components is very much correlated to the temperature environment in which they operate. This is no different for control system components, especially those with electronic parts. In recent years, the concept of Distributed Engine Control (DEC) has emerged to address the limitations of the current centralized control implementation. This new approach involves relocating control system components from a relatively benign environment to the harsher thermal environment of the engine casing and its surrounding structures and cavities. In this paper, an approach to modeling the gas turbine thermal environment is described. The modeling approach is applied to a 3rd generation geared turbofan design with a focus on the engine locations where control instrumentation and actuation could be installed. The analysis was conducted with an eye toward component reliability and service life as it relates to the thermal environment. The results were found to be reasonable. Furthermore, the model is shown to execute in real-time within a multi-model simulation environment that demonstrates the capability to interact with hardware to drive test equipment.
Document ID
Document Type
Kratz, Jonathan
(NASA Glenn Research Center Cleveland, OH, United States)
Culley, Dennis
(NASA Glenn Research Center Cleveland, OH, United States)
Thomas, George L.
(Vantage Partners, LLC Brook Park, OH, United States)
Date Acquired
October 24, 2018
Publication Date
July 10, 2018
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
Meeting Information
Meeting: AIAA Propulsion and Energy Forum
Location: Cincinnati, OH
Country: United States
Start Date: July 9, 2018
End Date: July 11, 2018
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 109492.
Distribution Limits
Public Use Permitted.
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