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Investigation of Afterburner Combustion Screech and Methods of Its Control at High Combustor Pressure LevelsVarious methods for the control of afterburner combustion screech at afterburner-inlet total pressures of from 4000 to 6400 pounds per square foot absolute were investigated experimentally. In general, the range of afterburner fuel- air ratios in which screech occurred and the intensity of screech did not vary appreciably in the range of pressures covered. However, several configurations which had mild screech tendencies at the lower pressures were screech-free, or nearly so, at higher pressure levels.

Screech was successfully eliminated over the range of pressures and fuel- air ratios investigated by several devices including a 20- inch length of corrugated louvered liner at the afterburner wall, a 7-inch perforated shroud around the outer ring of a 2-ring V- gutter flame holder, and a 2- ring V- gutter flame holder fabricated from perforated sheet metal. A 20-inch length of cylindrical liner spaced 5/8 inch from the afterburner wall and perforated with 3/16- inch- diameter holes on 1/2- inch centers did not entirely eliminate screech, but a 36- inch length of the same material did.
Document ID
19930089254
Acquisition Source
Glenn Research Center
Document Type
Other - NACA Research Memorandum
Authors
Arthur M. Trout
(Lewis Flight Propulsion Laboratory)
William K. Koffel
(Lewis Flight Propulsion Laboratory)
George R. Smolak
(Lewis Flight Propulsion Laboratory)
Date Acquired
August 16, 2013
Publication Date
May 14, 1956
Subject Category
Aircraft Design, Testing And Performance
Aircraft Propulsion And Power
Report/Patent Number
NACA-RM-E55k25
NACA-RM-E55K25
3943
Accession Number
93R18544
Funding Number(s)
TASK: Legacy Document
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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