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Altitude test of several afterburner configurations on a turbofan engine with a hydrogen heater to simulate an elevated turbine discharge temperatureA performance test of several experimental afterburner configurations was conducted with a mixed-flow turbofan engine in an altitude facility. The simulated flight conditions were for Mach 1.4 at two altitudes, 12,190 and 14,630 meters. Turbine discharge temperatures of 889 and 1056 K were used. A production afterburner was tested for comparison. The research afterburners included partial forced mixers with V-gutter flameholders, a carburetted V-gutter flameholder, and a triple ring V-gutter flameholder with four swirl-can fuel mixers. Fuel injection variations were included. Performance data shown include augmented thrust ratio, thrust specific fuel consumption, combustion efficiency, and total pressure drop across the afterburner.
Document ID
19780003163
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Johnsen, R. L. (NASA Lewis Research Center Cleveland, OH, United States)
Cullom, R. R. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
November 1, 1977
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
E-9207
NASA-TP-1068
Accession Number
78N11106
Funding Number(s)
PROJECT: RTOP 505-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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