Renas, Paul E., Braithwaite, Willis M., Jansen, Emmert T.
An investigation was conducted in an altitude chamber at the NACA Lewis laboratory to evaluate several afterburner configurations for a particular turbojet engine having a short converging conical afterburner shell with a two-position exhaust nozzle. Three configurations, which were designed on the basis of previous experiments with this burner, were installed. Performance characteristics and operational limits of each were obtained over a range of altitudes. An afterburner configuration was designed that had an operational limit of 51,000 feet with essentially no effect of altitude on performance up to an altitude of 45,000 feet. This configuration included a two-ring V-gutter flame holder, a streamlined diffuser inner body, 16 fuel-spray bars, and 37 turbine-outlet gas-flow straightening vanes.
An Adobe Acrobat (PDF) file of the entire report: