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An Adaptive Instability Suppression Controls Method for Aircraft Gas Turbine Engine CombustorsAn adaptive controls method for instability suppression in gas turbine engine combustors has been developed and successfully tested with a realistic aircraft engine combustor rig. This testing was part of a program that demonstrated, for the first time, successful active combustor instability control in an aircraft gas turbine engine-like environment. The controls method is called Adaptive Sliding Phasor Averaged Control. Testing of the control method has been conducted in an experimental rig with different configurations designed to simulate combustors with instabilities of about 530 and 315 Hz. Results demonstrate the effectiveness of this method in suppressing combustor instabilities. In addition, a dramatic improvement in suppression of the instability was achieved by focusing control on the second harmonic of the instability. This is believed to be due to a phenomena discovered and reported earlier, the so called Intra-Harmonic Coupling. These results may have implications for future research in combustor instability control.
Document ID
20080022424
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Kopasakis, George (NASA Glenn Research Center Cleveland, OH, United States)
DeLaat, John C. (NASA Glenn Research Center Cleveland, OH, United States)
Chang, Clarence T. (NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
August 24, 2013
Publication Date
May 1, 2008
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA/TM-2008-215202
E-16414-1
Funding Number(s)
WBS: WBS 984754.02.07.03.19.04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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