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NK-33
Credit - Karl Dodenhoff
Engine Model: NK-33. Manufacturer Name: NK-33. Government Designation: 11D111. Designer: Kuznetsov. Developed in: 1970-74. Application: N-1F stage 1 (block A). Propellants: Lox/Kerosene. Thrust(vac): 1,638.000 kN (368,237 lbf). Thrust(sl): 1,510.200 kN (339,506 lbf). Isp: 331 sec. Isp (sea level): 297 sec. Burn time: 600 sec. Mass Engine: 1,222 kg (2,694 lb). Diameter: 1.50 m (4.90 ft). Length: 3.71 m (12.17 ft). Chambers: 1. Chamber Pressure: 145.70 bar. Area Ratio: 27.00. Oxidizer to Fuel Ratio: 2.80. Thrust to Weight Ratio: 136.66. Country: Russia. Status: Design 1975.

After initial failures of N1 modified engines with multiple ignition capability and increased life were developed. NK-33 was tested at thrust of up to 204 t, variations of components ratio up to 20% and total burning time up to 1200 sec. Mothballed, never flown until selected by Kistler for their commercial launch vehicle in 1996.

Engine Model: NK-33 LH2 Mod + 4 x LACE. Manufacturer Name: NK-33 LH2 Mod. Designer: Kuznetsov. Developed in: 1974. Application: N1-MOK. Propellants: Air/Lox/LH2. Thrust(vac): 980.700 kN (220,470 lbf). Isp: 430 sec. Burn time: 410 sec. Chambers: 1. Country: Russia. Status: Study 1974.

Ultimate derivative of NK-9. Propellants changed to LH2/LOX, 16 x modified NK-33 engines + 4 Liquid Air Cycle Engine Liquid Air/LH2 boosters. All figures estimated based on tank volume of Block A and delivery of 90,000 kg payload to 400 kg MKBS orbit.

NK-33 used on Rocket Stages
  • Used on stage: N1-MOK. on launch vehicle: N1.
Bibliography:

  • Semenov, Yuri P Editor, Raketno-kosmicheskaya korporatsiya 'Energia' imeni S P Koroleva, Moscow, Russia, 1996.
  • Data sheets NPO Trud via Dietrich Haeseler.
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