RD-701
| Country of origin | USSR/Russia |
|---|---|
| Date | late 1980's |
| Manufacturer | Energomash |
| Successor | RD-704 |
| Status | Experimental |
| Liquid-fuel engine | |
| Propellant |
Mode#1: LOX / LH2&RP-1; Mode#2: LOX / LH2 |
| Cycle | staged combustion |
| Performance | |
| Thrust (vac.) |
Mode#1: 900,000 lbf (4 MN) Mode#2: 357,000 lbf (1.6 MN) |
| Thrust (SL) | Mode#1: 714,000 lbf (3.2 MN) |
| Chamber pressure |
Mode#1: 4,351 psi (30 MPa) Mode#2: 2,176 psi (15 MPa) |
| Isp (vac.) |
Mode#1: 415 s Mode#2: 460 s |
| Isp (SL) | Mode#1: 330 s |
| Dimensions | |
| Diameter | 94 in (2,400 mm) (1 nozzle) |
| Dry weight | 4,240 lb (1,923 kg) |
RD-701 (Russian: Раке́тный дви́гатель 701, Rocket Engine 701) - liquid-fuel rocket engine developed by Energomash, Russia. It was proposed to propel the reusable MAKS space plane before cancellation of this project. The RD-701 is a tripropellant engine that uses staged combustion cycle afterburning of oxidizer-rich hot turbine gas. This engine has two modes. Mode #1 uses three components: LOX as an oxidizer and a fuel mixture of RP-1 / LH2 which is applied for near earth surface conditions. Mode #2 also uses LOX, with LH2 as fuel in vacuum where atmospheric influence is negligible.
The use of less dense fuel components at maximum efficiency conditions allows minimizing the volume of fuel tanks and subsequently their mass down to 30%. As of 2009 the engine is characterized by highest value of pressure, 300 bar, ever used in combustion chamber of rocket engines when running in Mode #1 with mixture of fuel components. The RD-701 became the base model for RD-704 with one combustion chamber.
Two-chamber RD-701 has two modes. The first one uses three components: RP-1 (mass flow — 73.7 kg/s), LH2 (mass flow — 29.5 kg/s) and LOX (mass flow — 388.4 kg/s). This mode is applied in lower atmosphere to minimize fuel tanks volume. The total thrust for altitude 10 km is 2х1,890.2 KN and exhaust velocity is 3,845 m/s, giving a specific impulse of 392s.
...
Wikipedia