The Plug-Nozzle Rocket Engine
Although this engine is a liquid-propellant rocket, it substitutes a series of small combustion chambers and nozzles for the traditional single large chamber and nozzle to achieve additional thrust. This innovative combustion system features chambers and nozzles mounted on an annular ring at the base of the engine. Thrust is derived from the expansion of the exhaust gases against a large segmented plug in the center of the engine. Flight control is achieved by varying the amount of propellant introduced into the individual chamber sections. The engine on exhibit burned liquid oxygen and kerosene to provide a thrust of 22,680 kilograms (50,000 pounds).
The plug-nose rocket engine was developed at the General Electric Company’s Malta Test Station in 1961.
The engine on exhibit is from the New York State Atomic and Space Authority.