A rocket engine thrust nozzle assembly is disclosed wherein combustion products from a plurality of rocket engines having hexagonally-shaped exhaust areas flow to the inlet of a main nozzle that transitions the flow of the combustion products from a non-circular flow area to a circular flow area.
A thrust nozzle for a rocket engine comprising: a plurality of modular rocket engines clustered about a first axis that is perpendicular to a first plane, each modular rocket engine including a combustion chamber having a circular cross section and a circular discharge hole for discharging combustion products of the combustion chamber, and a modular nozzle having a modular nozzle inlet of the same diameter as the circular discharge hole and connected thereto for receiving the combustion products therefrom, and a modular nozzle outlet for discharging the ...
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