NASA Logo

NTRS

NTRS - NASA Technical Reports Server

As of October 27, 2023, NASA STI Services will no longer have an embargo for accepted manuscripts. For more information visit NTRS News.

Back to Results
A Dynamic Model for the Evaluation of Aircraft Engine Icing Detection and Control-Based Mitigation StrategiesAircraft flying in regions of high ice crystal concentrations are susceptible to the buildup of ice within the compression system of their gas turbine engines. This ice buildup can restrict engine airflow and cause an uncommanded loss of thrust, also known as engine rollback, which poses a potential safety hazard. The aviation community is conducting research to understand this phenomena, and to identify avoidance and mitigation strategies to address the concern. To support this research, a dynamic turbofan engine model has been created to enable the development and evaluation of engine icing detection and control-based mitigation strategies. This model captures the dynamic engine response due to high ice water ingestion and the buildup of ice blockage in the engines low pressure compressor. It includes a fuel control system allowing engine closed-loop control effects during engine icing events to be emulated. The model also includes bleed air valve and horsepower extraction actuators that, when modulated, change overall engine operating performance. This system-level model has been developed and compared against test data acquired from an aircraft turbofan engine undergoing engine icing studies in an altitude test facility and also against outputs from the manufacturers customer deck. This paper will describe the model and show results of its dynamic response under open-loop and closed-loop control operating scenarios in the presence of ice blockage buildup compared against engine test cell data. Planned follow-on use of the model for the development and evaluation of icing detection and control-based mitigation strategies will also be discussed. The intent is to combine the model and control mitigation logic with an engine icing risk calculation tool capable of predicting the risk of engine icing based on current operating conditions. Upon detection of an operating region of risk for engine icing events, the control mitigation logic will seek to change the engines operating point to a region of lower risk through the modulation of available control actuators while maintaining the desired engine thrust output. Follow-on work will assess the feasibility and effectiveness of such control-based mitigation strategies.
Document ID
20170009152
Document Type
Presentation
Authors
Simon, Donald L.
(NASA Glenn Research Center Cleveland, OH, United States)
Rinehart, Aidan W.
(Vantage Partners, LLC Cleveland, OH, United States)
Jones, Scott M.
(NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
September 28, 2017
Publication Date
June 26, 2017
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
GRC-E-DAA-TN43977
Meeting Information
Meeting: Turbo Expo: Turbomachinery Technical Conference & Exposition
Location: Charlotte, NC
Country: United States
Start Date: June 26, 2017
End Date: June 30, 2017
Sponsors: American Society of Mechanical Engineers
Funding Number(s)
CONTRACT_GRANT: NNC12BA01B
WBS: WBS 081876.02.03.50.08.02
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
engine control
gas turbine engines
engine icing
No Preview Available