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altitude investigation of several afterburner configurations for the j40-we-8 turbojet engineAn investigation was conducted in the Lewis altitude wind tunnel to evaluate the performance and operational characteristics of the J40-WE-8 afterburner. A brief program of minor modifications to the flame holder, diffuser, and fuel system was undertaken to improve at a burner-inlet pressure level of 620 pounds per square foot. At this pressure level, modifications to the fuel system resulted in an increase in maximum net thrust from 1500 to 1600 pounds and a reduction in specific fuel consumption in the stoichiometric region from 3.70 to 3.15 pounds of fuel per hour per pound of net thrust. However, these fuel system modifications also resulted in buzzing combustion under certain operation conditions.
Document ID
19930087411
Document Type
Other
Authors
Conrad, E William
Campbell, Carl E
Date Acquired
August 16, 2013
Publication Date
July 16, 1953
Report/Patent Number
NACA-RM-E52L10
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
COMBUSTION - EFFECT OF ENGINE OPERATING CONDITIONS AND COMBUSTION-CHAMBER GEOMET
DIFFUSERS, SUBSONIC
ENGINES, TURBOJET
TURBINES, GAS - AFTER-BURNING

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