Engine Model: RD-167. Manufacturer Name: RD-167. Designer: Glushko. Application: Upper stage. Propellants: Lox/LCH4. Thrust(vac): 353.000 kN (79,357 lbf). Isp: 379 sec. Mass Engine: 570 kg (1,250 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: 3.40. Thrust to Weight Ratio: 63.15. Country: Russia. Status: Design concept 1990's. Proposed upper stage engine, obviously a methane variant of RD-134. 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.
Bibliography:- 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.