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Demonstration of Active Combustion ControlThe primary objective of this effort was to demonstrate active control of combustion instabilities in a direct-injection gas turbine combustor that accurately simulates engine operating conditions and reproduces an engine-type instability. This report documents the second phase of a two-phase effort. The first phase involved the analysis of an instability observed in a developmental aeroengine and the design of a single-nozzle test rig to replicate that phenomenon. This was successfully completed in 2001 and is documented in the Phase I report. This second phase was directed toward demonstration of active control strategies to mitigate this instability and thereby demonstrate the viability of active control for aircraft engine combustors. This involved development of high-speed actuator technology, testing and analysis of how the actuation system was integrated with the combustion system, control algorithm development, and demonstration testing in the single-nozzle test rig. A 30 percent reduction in the amplitude of the high-frequency (570 Hz) instability was achieved using actuation systems and control algorithms developed within this effort. Even larger reductions were shown with a low-frequency (270 Hz) instability. This represents a unique achievement in the development and practical demonstration of active combustion control systems for gas turbine applications.
Document ID
20090010078
Acquisition Source
Glenn Research Center
Document Type
Contractor Report (CR)
Authors
Lovett, Jeffrey A.
(Pratt and Whitney Aircraft East Hartford, CT, United States)
Teerlinck, Karen A.
(United Technologies Research Center East Hartford, CT, United States)
Cohen, Jeffrey M.
(United Technologies Research Center East Hartford, CT, United States)
Date Acquired
August 24, 2013
Publication Date
December 1, 2008
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
E-16813
NASA/CR-2008-215491
Funding Number(s)
CONTRACT_GRANT: NAS3-98005
WBS: WBS 984754.02.07.03.19.04
Distribution Limits
Public
Copyright
Public Use Permitted.
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