RD-270
| Country of origin | USSR/Russia |
|---|---|
| Date | 1962-1968 |
| Designer | V. Glushko, USSR/Ukrainian Soviet Socialist Republic |
| Manufacturer | Energomash |
| Application | Glushko's answer to the US Rocketdyne_F-1 |
| Successor | RD-270M |
| Status | Development Cancelled in 1968 |
| Liquid-fuel engine | |
| Propellant | N2O4 / UDMH |
| Cycle | Full-flow staged combustion |
| Performance | |
| Thrust, vacuum | 6,713 kN (1,509,000 lbf) |
| Thrust, sea-level | 6,270 kN (1,410,000 lbf) |
| Thrust-to-weight ratio | 189.91 |
| Chamber pressure | 26.1 MPa (3,790 psi) |
| Specific impulse, vacuum | 322 s (3.16 km/s) |
| Specific impulse, sea-level | 301 s (2.95 km/s) |
| Dimensions | |
| Length | 194 in (4,900 mm) |
| Diameter | 132 in (3,400 mm) |
| Dry mass | 3,370 kg (7,430 lb) |
| Used in | |
| 1st stage of proposed UR-700 and UR-900 | |
RD-270 (Russian: Ракетный Двигатель-270, romanized: Raketnyy Dvigatel-270, lit. 'Rocket Engine 270', GRAU index: 8D420) was a single-chamber liquid-fuel rocket engine designed by Energomash (USSR) in 1960–1970. It was to be used on the first stages of the proposed heavy-lift UR-700 and UR-900 rocket families, as well as on the N1. It has the highest thrust among single-chamber engines of the USSR, 640 metric tons at the surface of Earth. The propellants used are a hypergolic mixture of unsymmetrical dimethylhydrazine (UDMH) fuel with dinitrogen tetroxide (N2O4) oxidizer. The chamber pressure was among the highest considered, being about 26 MPa. This was achieved by applying the full-flow staged combustion cycle for all the incoming mass of fuel, which is turned into a gas and passes through multiple turbines before being burned in the combustion chamber. This allowed the engine to achieve a specific impulse of 301 s (2.95 km/s) at the Earth's surface.
Engine testing was underway when the decision was made to cancel the program. Development was stopped with all other work on corresponding rocket projects on 11 December 1970.