RL10
Liquid fuel cryogenic rocket engine, typically used on rocket upper stages
Nº Q967724 ★
Common · Knowledge
RL10
Liquid fuel cryogenic rocket engine, typically used on rocket upper stages
The RL10 is a liquid-fuel cryogenic rocket engine built in the United States by Aerojet Rocketdyne that burns cryogenic liquid hydrogen and liquid oxygen propellants. Modern versions produce up to 110 kN (24,700 lbf) of thrust per engine in vacuum.
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From Wikipedia
The RL10 is a liquid-fuel cryogenic rocket engine built in the United States by Aerojet Rocketdyne that burns cryogenic liquid hydrogen and liquid oxygen propellants. Modern versions produce up to 110 kN (24,700 lbf) of thrust per engine in vacuum. RL10 versions were produced for the Centaur upper stage of the Atlas V and the DCSS of the Delta IV. More versions are in development or in use for the Space Launch System and the Centaur V of the Vulcan rocket. The expander cycle that the engine uses drives the turbopump with waste heat absorbed by the engine combustion chamber, throat, and nozzle. This, combined with the hydrogen fuel, leads to very high efficiency, with in-service variants achieving specific impulses (Isp) of up to 465.5 s (4.565 km/s) in a vacuum. Mass ranges from 131 to 317 kg (289–699 lb) depending on the version of the engine.
Text: Wikipédia, CC BY-SA 4.0. · Image: Les Chatfield (CC BY 2.0) ·
