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National Advisory Committee for Aeronautics, Research Memorandum - Experimental Investigation of Performance and Operating Characteristics of a Tail-Pipe Burner for a Turbojet Engine

An investigation has been conducted to obtain fundamental
information required for the design of a satisfactory tail—pipe
burner for augmenting the thrust of turbojet engines. The perform-
ance of 10 full scale tail pipe burners was investigated on a

blower rig and a description and the operating characteristics of'-
each are presented. Investigations were also conducted to determine
the'combustion and pressure—drop characteristics of the most satis-
factory burner, to develop a method of controlling the burner-outlet
temperature distribution, and to improve the burner ignition charac-
teristics.

A tail-pipe burner was developed that operated satisfactorily
over a range of fuel-air ratios with inlet conditions of gas temper-
ature and-velocity simulating these in a typical turbojet engine.
The average burner-outlet temperature was limited to about 21-100 F
because of the limited air pressure drop available for burning. The
performance of a similar tail-pipe burner , which incorporated the
principles and design features developed, was investigated con-
currently on a full- scale turbojet engine and operated satisfactorily
up to nearly stoichiometric fuel—air ratio with an estimated outlet
temperature of 35400F.

An investigation of various methods of thrust augmentation for
turbojet engines to improve the performance of Jet-propelled air-
planes for take-off, climb, and combat conditions is being conducted
at the NACA Cleveland laboratory. One method being investigated is
the burning of additional fuel in the tail pipe of the engine in
order to obtain higher gas temperatures than can be tolerated by the
turbine. These higher gas temperatures result in increased Jet
velocities and, consequently, increased thrust.