RD-134 (original) (raw)

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RD-134

Glushko LOx/Kerosene rocket engine. upper stage. Design concept. Proposed upper stage kerosene engine. Gimbaling +/- 3 degree in two planes. Four chamber s with one common turbopump. Nozzle expansion ratio is 170/0.05=3400.

Status: Design concept. Thrust: 343.00 kN (77,109 lbf). Unfuelled mass: 540 kg (1,190 lb). Specific impulse: 357 s. Height: 1.60 m (5.20 ft). Diameter: 2.40 m (7.80 ft).

In 1996 prototype development was estimated to take four years from go-ahead.

Chambers: 4. Engine: 540 kg (1,190 lb). Chamber Pressure: 167.00 bar. Thrust to Weight Ratio: 64.81. Oxidizer to Fuel Ratio: 2.6.

Subtopics

RD-134R Glushko LOx/Kerosene rocket engine. Angara stage 2 vernier. Design concept 1993-on. Proposed in initial study for Angara by RKK Energia in1993. Steering engines for Angara upper stage. Kerosene RG-1.

RD-167 Glushko LOx/LCH4 rocket engine. Upper stage. Design concept 1990's. Proposed upper stage engine, a methane variant of RD-134. Gimbaling +/- 3 degree in two planes. Four chambers with one common turbopump.

Country: Russia. Propellants: Lox/Kerosene. Agency: Glushko bureau. Bibliography: 21, 325.

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