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A Method for Prevention of Screaming in Rocket EnginesLateral and longitudinal combustion-pressure oscillations that occurred in screaming combustion of a 1000-pound-thrust rocket engine using white fuming nitric acid and JP-4 fuel as propellants were successfully prevented by means of longitudinal fins in the combustion chamber. Fin position was critical, and complete attenuation was achieved only when the fins were located in a zone approximately 8 to 16 inches from the injector. Fins located in other zones, that is, near the injector or far downstream from the injector, did not stop the oscillations. When oscillations occurred in finned chambers, the longitudinal mode seemed more dominant than the lateral mode; in chambers without fins, the lateral mode tended to be dominant. The lateral oscillation was distorted and its intensity diminished by the fins. Fins, however, did not affect the frequencies; the longitudinal frequency varied inversely with chamber length, and lateral frequencies varied only slightly from an average of 6000 cycles per second.
Document ID
19650013062
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Research Memorandum
Authors
Kerslake, W. R. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Male, T. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
August 19, 1954
Subject Category
Propulsion Systems
Report/Patent Number
NACA-RM-E54F28A
Accession Number
65N22663
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
ROCKET ENGINE NOISE
COMBUSTION CHAMBER
COMBUSTION INSTABILITY
PRESSURE OSCILLATION
FIN

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