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Effect of Diffuser Design, Diffuser-exit Velocity Profile and Fuel Distribution on Altitude Performance of Several Afterburner ConfigurationsAn investigation was conducted in the NACA Lewis altitude wind tunnel to improve the altitude performance and operational characteristics of an afterburner primarily by modifying the diffuser-exit velocity profile by changes in diffuser design and by changing the fuel distribution and the flame holder. Twenty configurations, consisting of combinations of six diffuser geometries, six flame-holder types, and twelve fuel systems, were investigated. Data were obtained over a range of afterburner fuel-air ratios at diffuser-inlet total pressures from 2750 to 620 pounds per square foot. Changes in fuel distribution affected the fuel-air ratio at which peak combustion efficiency occurred as well as the efficiency level. Screeching combustion, which was most prevalent at low altitudes and medium-to-high fuel-air ratios, imposed a restriction on the operable range of a number of configurations.
Document ID
19930089069
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Conrad, E William
Schultz, Frederick W
Usow, Karl H
Date Acquired
August 16, 2013
Publication Date
July 9, 1953
Report/Patent Number
NACA-RM-E53A30
Accession Number
93R18359
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
Diffusers, Subsonic
Combustion - Effect of Engine Operating Conditions and Combustion-Chamber Geomet
Fuels - Relation to Engine Performance
Turbine, Gas - Afterburning

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