A liquid propellant rocket engine includes a combustion chamber that has a throat and a nozzle aft of the throat. The nozzle has a first nozzle section adjacent the throat and a second nozzle section aft of the first nozzle section. The first nozzle section includes active cooling features and the second nozzle section excludes any active cooling features. The first nozzle section is operative via at least the active cooling features to form a condensate that passively cools the second nozzle section.
Liquid propellant rocket engine nozzle with passive condensate cooling
2021-03-23
Patent
Elektronische Ressource
Englisch
Europäisches Patentamt | 2021
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