RD-0124

RD-0124 (14D23)
	RD-0124 model on display at the 2013 Paris Air Show
Country of origin	Russia
Date	1993–2006
First flight	2006-12-27
Designer	Valery Kozelkov and Viktor Gorokhov)
Manufacturer	Chemical Automatics Design Bureau
Application	Upper stage engine
Associated LV	Current: Angara, Soyuz-2.1b, Soyuz-2.1v; Planned: Soyuz 5
Predecessor	RD-0110
Status	In production
Liquid-fuel engine
Propellant	LOX / RP-1
Cycle	Staged combustion
Configuration
Chamber	4
Performance
Thrust, vacuum	294.3 kN (66,200 lbf)
Thrust-to-weight ratio	52.5
Chamber pressure	15.7 MPa (2,280 psi)
Specific impulse, vacuum	359 s (3.52 km/s)
Burn time	RD-0124: 270 seconds; RD-0124A: 424 seconds
Dimensions
Length	1,575 mm (62.0 in)
Diameter	2,400 mm (94 in)
Dry mass	RD-0124: 572 kg (1,261 lb) ; RD-0124A: 548 kg (1,208 lb)
Used in
	Soyuz 2.1b / Soyuz 2.1v Block I stage; Angara URM-2 stage
References
References

The RD-0124 (Russian: Ракетный Двигатель-0124, romanized: Raketnyy Dvigatel-0124, lit. 'Rocket Engine 0124', GRAU index: 14D23) is a rocket engine burning liquid oxygen and kerosene in an oxygen-rich staged combustion cycle, developed by the Chemical Automatics Design Bureau in Voronezh. RD-0124 engines are used on the Block I stage used on Soyuz-2.1b and Soyuz-2.1v. A variant of the engine, the RD-0124A, is used on the Angara rocket family's URM-2 upper stage.

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^ Zak, Anatoly (April 4, 2024). "RD-0124 engine". RussianSpaceWeb.com. Retrieved 2024-11-27.