RD-253
Soviet engine design used on the first stage of Proton rockets / From Wikipedia, the free encyclopedia
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The RD-253 ( Russian: Раке́тный дви́гатель 253 , Rocket Engine 253) and its later variants, the RD-275 and RD-275M, are liquid-propellant rocket engines developed in the Soviet Union by Energomash. The engines are used on the first stage of the Proton launch vehicle and use an oxidizer-rich staged combustion cycle to power the turbopumps. The engine burns UDMH/N2O4, which are highly toxic but hypergolic and storable at room temperature, simplifying the engine's design.
Quick Facts Country of origin, First flight ...
Country of origin | USSR/Russia |
---|---|
First flight | RD-253: 1965 RD-275: 1995 RD-275М: 2007 |
Designer | Energomash, V.Glushko |
Manufacturer | Proton-PM |
Application | First stage booster |
Associated LV | Proton |
Successor | RD-254, RD-256, RD-275, RD-275М |
Status | Operational |
Liquid-fuel engine | |
Propellant | N2O4 / UDMH |
Mixture ratio | 2.67 |
Cycle | Staged combustion |
Configuration | |
Chamber | 1 |
Nozzle ratio | 26.2 |
Performance | |
Thrust, vacuum | RD-253: 1,630 kN (370,000 lbf) RD-275: 1,750 kN (390,000 lbf) RD-275М: 1,832 kN (412,000 lbf) |
Thrust, sea-level | RD-253: 1,470 kN (330,000 lbf) RD-275: 1,590 kN (360,000 lbf) RD-275М: 1,671 kN (376,000 lbf) |
Thrust-to-weight ratio | 156.2 |
Chamber pressure | RD-253: 14.7 MPa (2,130 psi; 147 bar) RD-275: 15.7 MPa (2,280 psi; 157 bar) RD-275M: 16.5 MPa (2,390 psi; 165 bar) |
Specific impulse, vacuum | RD-253: 316s RD-275: 316s RD-275M: 315.8s |
Specific impulse, sea-level | RD-253: 285s RD-275: 287s RD-275M: 288s |
Gimbal range | 7.5°, single plane |
Dimensions | |
Length | 3 m (9.8 ft) |
Diameter | 1.5 m (4 ft 11 in) |
Dry weight | RD-253: 1,080 kg (2,380 lb) RD-275: 1,070 kg (2,360 lb) RD-275M: 1,070 kg (2,360 lb) |
Used in | |
Proton first stage. | |
References | |
References | [1][2][3][4][5][6][7] |
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