Application of Gas-Film-Cooled Nozzle Extensions to Large Rocket Engines 660455
During the F-1 rocket engine program, turbine exhaust gases have been successfully used to film cool large thrust chamber nozzle extensions. This design concept provides the engine with a detachable nozzle of low weight, simple construction, and a service life equivalent to that of the basic engine.
Several nozzle extension concepts are reviewed, and a comparison is made in terms of operational advantages and engine application as defined by required nozzle geometry, heat flux, and available coolant. The particular application for which the gas-cooled concept is the most desirable engineering choice is discussed in detail.
Experimental data obtained during development are presented, with particular emphasis given to thermal analysis considerations. The correlation observed between predicted and measured temperatures is also discussed.
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