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Engine Model: RD-134. Manufacturer Name: RD-134. Designer: Glushko. Application: upper stage. Propellants: Lox/Kerosene. Thrust(vac): 343.000 kN (77,109 lbf). Isp: 357 sec. Mass Engine: 540 kg (1,190 lb). Diameter: 2.40 m (7.80 ft). Length: 1.60 m (5.20 ft). Chambers: 4. Chamber Pressure: 167.00 bar. Oxidizer to Fuel Ratio: 2.60. Thrust to Weight Ratio: 64.81. Country: Russia. Status: Design concept.

Proposed upper stage kerosene engine. Gimbaling +/- 3 degree in two planes. Status 1996 was project, development estimated for four years. Four chamber s with one common turbopump. Nozzle expansion ratio is 170/0.05=3400.

Engine Model: RD-134R. Manufacturer Name: RD-134R. Government Designation: 11D123. Other Designations: RD-123. Designer: Glushko. Developed in: 1993. Application: Angara stage 2 vernier. Propellants: Lox/Kerosene. Thrust(vac): 343.000 kN (77,109 lbf). Chambers: 4 (?). Country: Russia. Status: Design concept 1993-on.

Proposed in initial study for Angara by RKK Energia in1993. Steering engines for Angara upper stage. Kerosene RG-1.

Bibliography:

  • Semenov, Yuri P Editor, Raketno-kosmicheskaya korporatsiya 'Energia' imeni S P Koroleva, Moscow, Russia, 1996.
  • Klepikov, Katorgin, Chvanov, IAF-Congress Turin, 1997, "The New Generation of Rocket Engines, Operating by Ecologically Safe Propellant ...", IAF-97-S.1.03 via Dietrich Haeseler.
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