RD-270
| Country of origin | USSR/Russia |
|---|---|
| Date | 1969 |
| Designer | V. Glushko, USSR/Ukraine |
| Manufacturer | Energomash |
| Successor | RD-270M |
| Status | Retired |
| Liquid-fuel engine | |
| Propellant | N2O4 / UDMH |
| Cycle | Full-flow staged combustion |
| Performance | |
| Thrust (vac.) | 6,710 kN (1,510,000 lbf) |
| Thrust (SL) | 6,270 kN (1,410,000 lbf) |
| Thrust-to-weight ratio | 189.91 |
| Chamber pressure | 26.1 MPa (3,790 psi) |
| Isp (vac.) | 322 s (3.16 km/s) |
| Isp (SL) | 301 s (2.95 km/s) |
| Dimensions | |
| Length | 194 in (4,900 mm) |
| Diameter | 132 in (3,400 mm) |
| Dry weight | 3,370 kg (7,430 lb) |
| Used in | |
| 1st stage of proposed UR-700 and UR-900 | |
RD-270 (Russian: Ра́кетный дв́игатель 270, Rocket Engine 270, 8D420) is a single-chamber liquid-bipropellant rocket engine designed by Energomash (USSR/Russia) in 1960–1970. It was to be used on the first stages of proposed heavy-lift UR-700 and UR-900 rocket families. It has the highest thrust among single-chamber engines of USSR and Russia, 640 metric tons at the surface of Earth. The propellants used are unsymmetrical dimethylhydrazine (UDMH) and nitrogen tetroxide (N2O4). The chamber pressure is among the highest, being about 26 MPa. This was achieved by applying full-flow staged combustion cycle for all the incoming mass of fuel, which is turned into a gas and passes through a couple of turbines before being burned in the combustion chamber. This allows it to achieve a specific impulse of 301 s (2.95 km/s) at the Earth's surface.
The engine testing was underway when the decision was made to cancel the program. The development of it was stopped with all other work on corresponding rocket projects on 11 December 1970.
The development of RD-270 started on 26 June 1962. Preliminary investigations and development of engine as much as its further production was performed under the guidance of Valentin Glushko and finished in 1967. It became the most powerful engine in the world with use of high-boiling propellant to date. In the period 1967–1969, several fire tests were performed with experimental engines that were adapted for work at sea level and had short nozzle. In total, 27 fire tests were performed for 22 engines, three engines were tested twice, and one of them was tested three times. All works stopped later together with corresponding activities on UR-700 project.
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