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RD-120K
Part of RD-120 Family
Glushko LOx/Kerosene rocket engine. Soyuz M stage 1, 2. Proposed for X-34. Sea-level variant of RD-120. As of 1996 RD-120 prototype with 1.8 m diameter had been built, development time estimated for three years.

AKA: RD-123. Status: Design 1994. Thrust: 873.00 kN (196,258 lbf). Unfuelled mass: 1,433 kg (3,159 lb). Specific impulse: 336 s. Specific impulse sea level: 298 s. Burn time: 305 s. Height: 2.80 m (9.10 ft). Diameter: 1.50 m (4.90 ft).

Thrust and Isp range due to throat diameter and chamber pressure. Gimbaling +/- 6 degree in two planes. Chamber pressure 163 - 172 bar.

Throttled thrust(vac): 794.000 kN (178,498 lbf). Thrust (sl): 866.900 kN (194,887 lbf). Thrust (sl): 88,396 kgf. Engine: 1,433 kg (3,159 lb). Chamber Pressure: 172.00 bar. Thrust to Weight Ratio: 62.1. Oxidizer to Fuel Ratio: 2.6.



Country: Russia. Launch Vehicles: Soyuz M. Propellants: Lox/Kerosene. Stages: Kvant-1 stage, Kvant-1-1, Soyuz M-0, Soyuz M-1. Agency: Glushko bureau.

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