This page no longer updated from 31 October 2001. Latest version can be found at RD-134

Manufacturer Name: RD-134. Designer: Glushko. Application: upper stage. Propellants: Lox/Kerosene Thrust(vac): 35,000 kgf. Thrust(vac): 343.00 kN. Isp: 357 sec. Mass Engine: 540 kg. Diameter: 2.4 m. Length: 1.6 m. Chambers: 4. Chamber Pressure: 167.00 bar. Oxidizer to Fuel Ratio: 2.60. Country: Russia. Status: Design concept. References: 325 . Comments: 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.
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Last update 12 March 2001.
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© Mark Wade, 2001 .