Experimental performance of the mixed-oxides-of-nitrogen-ammonia propellant combination in a 1000-pound-thrust rocket engine Page: 4 of 32
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NACA RM E55A07 3
The propellants were fed to the engine from helium-pressurized
tanks; the flow rates were controlled by tank pressure. Firing opera-
tions were accomplished by remotely controlled valves. A chamber was
provided between the fuel-control valve and the engine to hold lithium,
which was used to obtain spontaneous ignition as in reference 2. All
components of both fuel and oxidant flow systems were of stainless steel.
Engine and Mounting
The engine was mounted on a movable stand supported on two steel
flexure plates perpendicular to it. The stand was inclined downward at
an angle of 300.
The engine (fig. 1) consisted of an uncooled steel chamber 4 inches
in diameter and 13 inches long, and an uncooled copper nozzle. Most of
the runs were made using a nozzle designed for 1000 pounds thrust at a
chamber pressure of 300 pounds per square inch absolute. One set of runs
4 was made using a nozzle designed for 350 pounds thrust at a chamber pres-
sure of 300 pounds per square inch absolute.
Four-entry swirl cup. - The four-entry swirl cup (fig. 2) had two
fuel and two oxidant entries arranged alternately about the cup 900
apart. The entry holes were tangent to the circumference of the cup and
l00 from normal to the axis pointing out of the cup. The cup length was
twice the cup diameter. Water-flow tests at rated flows showed a pres-
sure drop of 100 pounds per square inch for the oxidant and 10 pounds
per square inch for the fuel. However, during operation, equivalent
flows gave pressure drops of 290 pounds per square inch for the oxidant
and 310 pounds per square inch for the fuel, because the pressure in
the swirl cup was probably considerably higher than the chamber pressure.
Triplet impinging jet injector. - Figure 3 shows the triplet imping-
ing jet injector. It had 120 oxidant holes of 0.037-inch diameter and
60 fuel holes of 0.047-inch diameter. The injector face consisted of
five 0.75-inch mild-steel tubes, three for oxidant and two for fuel with
fuel and oxidant tubes alternating. Six groups of ten triplet sets each
were arranged in two parallel rows across the injector face. Rated flows
were obtained at a pressure drop of 100 pounds per square inch.
Hot-jet mixing injector. - The hot-jet mixing injector (fig. 4)
consisted of an antechamber in which approximately 10 percent of the
total flow was burned and a second chamber in which the remainder of the
flow was introduced through drilled tubes into the hot jet issuing from
the antechamber. The tubes could be rotated to produce different flow
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Tomazic, William A. & Kinney, George R. Experimental performance of the mixed-oxides-of-nitrogen-ammonia propellant combination in a 1000-pound-thrust rocket engine, report, March 28, 1955; (digital.library.unt.edu/ark:/67531/metadc61181/m1/4/: accessed December 16, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.