RD-57 home
topic index
Engine Model: RD-57. Manufacturer Name: RD-57. Government Designation: 11D57. Other Designations: D-57. Designer: Lyulka. Developed in: 1960-77. Application: N1 Block S (N-1M). Propellants: Lox/LH2. Thrust(vac): 392.000 kN (88,125 lbf). Isp: 457 sec. Burn time: 800 sec. Mass Engine: 840 kg (1,850 lb). Diameter: 1.86 m (6.10 ft). Length: 3.66 m (12.00 ft). Chambers: 1. Chamber Pressure: 111.00 bar. Area Ratio: 142.30. Oxidizer to Fuel Ratio: 5.80. Thrust to Weight Ratio: 47.61. Country: Russia. Status: Study 1965.

One to have been used in N1 Block S. In fixed chamber version, 3 to 6 to have been used in N1 Block V-III. Engine system includes roll control thruster with 1.29 kN thrust.

Engine Model: RD-57A-1. Manufacturer Name: RD-57A-1. Designer: Lyulka. Developed in: 1995-98. Propellants: Lox/LH2. Thrust(vac): 395.000 kN (88,799 lbf). Isp: 460 sec. Mass Engine: 550 kg (1,210 lb). Diameter: 1.85 m (6.06 ft). Length: 3.15 m (10.33 ft). Chambers: 1. Area Ratio: 143.00. Oxidizer to Fuel Ratio: 5.80. Thrust to Weight Ratio: 73.23. Country: Russia. Status: Developed 1995-98.

New version of RD-57M for SSTO-demonstrator proposed by Aerojet. Optimized nozzle contour for performance increase, new chamber material for weight reduction. First launch was planned for 3rd quarter 1998 in 1994, but not performed until 1999.

Engine Model: RD-57M. Manufacturer Name: RD-57M. Government Designation: 11D57M. Designer: Lyulka. Developed in: 1960-74. Application: Vulkan Blok V. Propellants: Lox/LH2. Thrust(vac): 397.000 kN (89,249 lbf). Throttled thrust(vac): 303.000 kN (68,117 lbf). Isp: 461 sec. Mass Engine: 874 kg (1,926 lb). Diameter: 2.00 m (6.50 ft). Length: 4.06 m (13.32 ft). Chambers: 1. Chamber Pressure: 115.00 bar. Area Ratio: 170.00. Oxidizer to Fuel Ratio: 6.20. Thrust to Weight Ratio: 46.31. Country: Russia. Status: Development ended 1976.

Version with extendible nozzle. Ref. Lyulka 94 has higher mass at 911 kg and higher fixed nozzle area ratio at 100. Length 4.06 / 2.61 m. Specific impulse 461 / 448 sec. Area ratio 170 / 87.6.

RD-57 used on Rocket Stages
  • Used on stage: N1-S. on launch vehicle: N1.
Bibliography:

  • Semenov, Yu. P., S P Korolev Space Corporation Energia, RKK Energia, 1994.
  • Zhelyeznakov, "Personal communication.",
  • Haeseler, Dietrich, Presentation of demonstrator via Dietrich Haeseler.
  • Andreeyev, Chepkin, Fanciullo, AIAA Joint Prop. Conf., June 1994, "The Development of the D-57 Advanced Staged Combustion Engine for Upper stages", AIAA-94, AIAA Joint Prop. Conf., June 1994 via Dietrich Haeseler.
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