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A Parametric Study of Actuator Requirements for Active Turbine Tip Clearance Control of a Modern High Bypass Turbofan EngineThe efficiency of aircraft gas turbine engines is sensitive to the distance between the tips of its turbine blades and its shroud, which serves as its containment structure. Maintaining tighter clearance between these components has been shown to increase turbine efficiency, increase fuel efficiency, and reduce the turbine inlet temperature, and this correlates to a longer time-on-wing for the engine. Therefore, there is a desire to maintain a tight clearance in the turbine, which requires fast response active clearance control. Fast response active tip clearance control will require an actuator to modify the physical or effective tip clearance in the turbine. This paper evaluates the requirements of a generic active turbine tip clearance actuator for a modern commercial aircraft engine using the Commercial Modular Aero-Propulsion System Simulation 40k (C-MAPSS40k) software that has previously been integrated with a dynamic tip clearance model. A parametric study was performed in an attempt to evaluate requirements for control actuators in terms of bandwidth, rate limits, saturation limits, and deadband. Constraints on the weight of the actuation system and some considerations as to the force which the actuator must be capable of exerting and maintaining are also investigated. From the results, the relevant range of the evaluated actuator parameters can be extracted. Some additional discussion is provided on the challenges posed by the tip clearance control problem and the implications for future small core aircraft engines.
Document ID
20170008736
Document Type
Conference Paper
Authors
Kratz, Jonathan L.
(NASA Glenn Research Center Cleveland, OH United States)
Chapman, Jeffryes W.
(Vantage Partners, LLC Cleveland, OH, United States)
Guo, Ten-Huei
(NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
September 11, 2017
Publication Date
June 26, 2017
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
GT2017-63472
GRC-E-DAA-TN39865
Meeting Information
Meeting: ASME 2017 Turbo Expo
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 081876.02.03.50.04.02
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
Turbine
Tip Clearance
Control
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