Experimental investigation of thrust augmentation of a turbojet engine at zero ram by means of tail-pipe burning Page: 3 of 37
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NACA RM No. ESJ21
The inherently low propulsive efficiency of turbojet engines at
low flight speeds results in relatively poor take-off and climb
characteristics of jet-propelled aircraft as compared with conven-
tional engine-propeller powered aircraft. In order to improve the
low-speed flight characteristics of jet-propelled aircraft, it is
necessary to augment the normal engine thrust for short periods of
time. The availability of momentary thrust augmentation is partic-
ul.arly desirable for military aircraft in order to obtain the addi-
tional thrust required for high-speed flight.
An investigation of various methods of augmenting the thrust of
turbojet engines is being conducted at the NACA Cleveland laboratory.
One of the methods being investigated is tail-pipe burning, or after-
burning, wherein the gas temperatures and jet velocities are increased
by the burning of additional fuel in the tail pipe of the engine. This
method of thrust augmentation is particularly advantageous because of
the ease of operation and relatively low liquid consumption as compared
with other methods. Because only a small amount of additional equip-
ment is required for the tail-pipe-burner installation, which consists
mainly of an adjustable-area exhaust nozzle and enlarged tail pipe
incorporating fuel nozzles and a flame holder, this method also has
the practical advantage of simplicity of installation.
A wind-tunnel investigation of a turbojet engine equipped with a
tail-pipe burner, which was conducted under various flight and alti-
tude conditions, is described in reference 1. A concurrent investi-
gation of the performance of various other types of tail-pipe burner
was conducted at zero ram and sea-level conditions. The tail-pipe
burner incorporating the most satisfactory design features investi-
gated and the performance of a turbojet engine equipped with this
burner are described. This performance investigation covered a range
of rotor speeds and tail-pipe-burner fuel flows. The results are
compared with the performance of the engine with the standard tail
pipe and the effect of the tail-pipe burner without afterburning on
the thrust of the engine is evaluated.
Test engine. - The performance of the tail-pipe burner was inves-
tigated on a TG-180 turbojet engine, which has an 11-stage axial-flow
compressor, eight cylindrical combustion chambers, and a single-stage
turbine. The rating of the engine is as follows:
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Lundin, Bruce T.; Dowman, Harry W. & Gabriel, David S. Experimental investigation of thrust augmentation of a turbojet engine at zero ram by means of tail-pipe burning, report, January 6, 1947; (digital.library.unt.edu/ark:/67531/metadc58109/m1/3/: accessed December 16, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.