RD-191
The RD-191 (Russian: РД-191, Ракетный Двигатель-191, lit. 'Rocket Engine 191') is a high-performance single-combustion chamber rocket engine, developed in Russia. It is derived from the RD-180 dual-combustion chamber engine, which itself was derived in turn from the four-chamber RD-170 originally used in the Energia launcher.
| Country of origin | Russia |
|---|---|
| Date | 2001 |
| Designer | NPO Energomash |
| Manufacturer | NPO Energomash / Proton-PM (in transition) |
| Application | Main engine |
| Predecessor | RD-170 |
| Status | In use |
| Liquid-fuel engine | |
| Propellant | LOX / RP-1 |
| Mixture ratio | 2.6 |
| Cycle | Oxidizer-rich staged combustion |
| Configuration | |
| Nozzle ratio | 37:1 |
| Performance | |
| Thrust, vacuum | 2.09 MN (470,000 lbf) at 100% throttle |
| Thrust, sea-level | 1.92 MN (432,000 lbf) at 100% throttle |
| Throttle range | 27–105% |
| Thrust-to-weight ratio | 89 |
| Chamber pressure | 25.8 MPa (3,740 psi) |
| Specific impulse, vacuum | 337 s (3.30 km/s) |
| Specific impulse, sea-level | 310.7 s (3.047 km/s) |
| Burn time | 325 s (Angara A5 core stage) |
| Gimbal range | 8° |
| Dimensions | |
| Length | 4 m (160 in) |
| Diameter | 1.45 m (57 in) |
| Dry weight | 2,290 kg (5,050 lb) |
| References | |
| References | |
The RD-191 is fueled by a kerosene / LOX mixture and uses an oxygen-rich staged combustion cycle. In the future the engine is expected to become a workhorse in the Russian space sector, as older launch vehicles are phased out of production and service.
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