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Fuel Line Based Acoustic Flame-Out Detection SystemAn acoustic flame-out detection system that renders a large high pressure combustor safe in the event of a flame-out and possible explosive reignition. A dynamic pressure transducer is placed in the fuel and detects the stabilizing fuel pressure oscillations, caused by the combustion process. An electric circuit converts the signal from the combustion vortices, and transmitted to the fuel flow to a series of pulses. A missing pulse detector counts the pulses and continuously resets itself. If three consecutive pulses are missing, the circuit closes the fuel valve. With fuel denied the combustor is shut down or restarted under controlled conditions.
Document ID
19980032582
Acquisition Source
Langley Research Center
Document Type
Other - Patent
Authors
Puster, Richard L.
(NASA Langley Research Center Hampton, VA United States)
Franke, John M.
(NASA Langley Research Center Hampton, VA United States)
Date Acquired
August 18, 2013
Publication Date
September 9, 1997
Subject Category
Instrumentation And Photography
Report/Patent Number
Patent Application Number: US-Patent-Appl-SN-672294
Patent Number: US-Patent-5,665,916
Patent Number: NASA-Case-LAR-15296-1
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
US-Patent-5,665,916|NASA-Case-LAR-15296-1
Patent Application
US-Patent-Appl-SN-672294
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