Liquid fuel cryogenic rocket engine, typically used on rocket upper stages
This article needs to be updated. The reason given is: Info on improvement projects is dated. Please help update this article to reflect recent events or newly available information.(June 2020)
RL10
An RL10A-4 engine in London's Science Museum
Country of origin
United States of America
First flight
1962 (RL10A-1)
Manufacturer
Aerojet Rocketdyne
Application
Upper stage engine
Associated LV
Atlas Saturn I Titan IIIE Titan IV Delta III Delta IV DC-X (canceled) Space Shuttle (canceled) Space Launch System OmegA (canceled) Vulcan
Status
In production
Liquid-fuel engine
Propellant
Liquid oxygen / liquid hydrogen
Mixture ratio
5.88:1
Cycle
Expander cycle
Configuration
Nozzle ratio
84:1 or 280:1
Performance
Thrust, vacuum
110.1 kN (24,800 lbf)
Specific impulse, vacuum
465.5 seconds (4.565 km/s)
Dimensions
Length
4.15 m (13.6 ft) w/ nozzle extended
Diameter
2.15 m (7 ft 1 in)
Dry weight
301 kg (664 lb)
Used in
Centaur, DCSS, S-IV
References
References
[1]
Notes
Performance values and dimensions are for RL10B-2.
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 (24,729 lbf) of thrust per engine in vacuum. Three RL10 versions are in production for the Centaur upper stage of the Atlas V and the DCSS of the Delta IV. Three more versions are in development for the Exploration Upper Stage of the Space Launch System and the Centaur V of the Vulcan rocket.[2]
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 specific impulses (Isp) in the range of 373 to 470 s (3.66–4.61 km/s) in a vacuum. Mass ranges from 131 to 317 kg (289–699 lb) depending on the version of the engine.[3][4]
^Cite error: The named reference EA10B2 was invoked but never defined (see the help page).
^Cite error: The named reference :1 was invoked but never defined (see the help page).
^"RL-10C". www.astronautix.com. Archived from the original on December 28, 2016. Retrieved April 6, 2020.
^"RL-10A-1". www.astronautix.com. Archived from the original on December 28, 2016. Retrieved April 6, 2020.
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...
up. Some examples of an expander cycle engine are the Aerojet Rocketdyne RL10 and the Vinci engine for the future Ariane 6. This operational cycle is a...
improved version of the Centaur III used on the Atlas, which is powered by two RL10 engines built by Aerojet Rocketdyne, fueled by liquid hydrogen and liquid...
150 s Fuel: RP-1 / LOX The S-IV stage was powered by six LOX / LH2-fueled RL10 engines, mounted on gimbals. The propellant tanks used a single, common bulkhead...
the Aerojet Rocketdyne RL10, providing improved performance and efficiency while maintaining the installation envelope of the RL10. RL60 was planned to...
2016, it was reported that NASA has chosen to use a design based on four RL10-C3 engines for the EUS, and in October 2016 NASA confirmed they had ordered...
international customers. RL10 cryogenic flow control valves Atec has manufactured, assembled, and tested cryogenic flow control valves for the RL10 liquid-fueled...
liquid oxygen. The Centaur upper stage is powered by one or two American RL10 engine(s) manufactured by Aerojet Rocketdyne and burns liquid hydrogen and...
Tim Dodd Dodd with RL10 rocket engine in June 2021 Born (1985-02-27) February 27, 1985 (age 39) Iowa Nationality American Occupation Science communicator...
already in use in the Titan booster by 1968 and had been tested with the RL10 engine, demonstrating its suitability for upper stage engines. Traditionally...
human-rated Delta IV 16 ft (5 m) Delta Cryogenic Second Stage powered by a single RL10 engine. The Artemis 1 ICPS used the RL10B-2 variant, while the ICPS for Artemis...
Under the new plan, Vulcan's upper stage is the Centaur V, with two LH2/LOX RL10 engines and no IVF or other ACES extended-duration technology as had been...
expendable version, RS-25E will be developed for follow-on SLS launches. RL10 (LHLH2/LOX) – Developed by Pratt & Whitney and currently used on the Centaur...
(Hughes HME-5118ME system) NATO Air Defence Ground Environment (NADGE) system RL10 rocket engines Civil NAS (National Airspace System) Air Traffic Control APG-70...
for helping develop the model 304 liquid hydrogen aircraft engine and the RL10 rocket engine. He was later executive vice president at Pratt & Whitney....
integration. Like the earlier DCSS, the ICPS is powered by one Aerojet Rocketdyne RL10 engine and generates 110.1 kilonewtons (24,800 pounds-force) of maximum thrust...
Archived from the original on February 25, 2022. Retrieved January 19, 2020. "RL10 Data Sheet-1" (PDF). February 2016. Archived from the original (PDF) on July...
Global Information
