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Manufacturer Name: RD-0124. Government Designation: 14D451M. Other Designations: 14D23. Designer: Kosberg. Developed in: 1993-. Application: Rus Soyuz 2 stage 3. Propellants: Lox/Kerosene Thrust(vac): 30,000 kgf. Thrust(vac): 294.30 kN. Isp: 359 sec. Isp (sea level): 331 sec. Burn time: 300 sec. Mass Engine: 480 kg. Diameter: 2.4 m. Length: 1.6 m. Chambers: 4. Chamber Pressure: 157.00 bar. Oxidizer to Fuel Ratio: 2.60. Country: Russia. Status: Developed 1993-. First Flight: 1998. References: 225 , 226 , 312 . Comments: Engine to succeed RD-0110 in second stage of Soyuz-2/Rus LV. Uses staged combustion; chamber pressure increased from 70 to 160 atmospheres, specific impulse from 326 to 359 seconds, payload by 950 kg from current 6900/7200 kg (Plesetsk/Baikonur).
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Last update 12 March 2001.
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