|Country of origin||USSR/Russia|
|First flight||RD-253: 1965|
|Application||First stage booster|
|Successor||RD-254, RD-256, RD-275, RD-275?|
|Propellant||N2O4 / UDMH|
|Thrust (vac.)||RD-253: 1,630 kN (370,000 lbf)|
RD-275: 1,750 kN (390,000 lbf)
RD-275?: 1,832 kN (412,000 lbf)
|Thrust (SL)||RD-253: 1,470 kN (330,000 lbf)|
RD-275: 1,590 kN (360,000 lbf)
RD-275?: 1,671 kN (376,000 lbf)
|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)
|Isp (vac.)||RD-253: 316s|
|Isp (SL)||RD-253: 285s|
|Gimbal range||7.5°, single plane|
|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)
|Proton first stage.|
The RD-253 ( Russian: ? 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 design.
Development of the RD-253 started in 1961. Preliminary investigations and development of the engine as well as its further production was performed under the guidance of Valentin Glushko and finished in 1963. The RD-253 uses a staged combustion cycle for oxidizer-rich generator gas. It was used for the first time in July 1965 when six engines powered the first stage of the rocket. Development and production of RD-253 was a qualitative leap forward for rocketry of that time by achieving high levels of thrust, specific impulse and pressure in the combustion chamber. This engine is one of the most reliable engines in the USSR and modern Russia.
As every first stage of Proton-K rockets used six RD-253 engines, the system played a pivotal role in Russian space missions when this rocket was chosen as carrier, including the following programs: "Luna", "Venera", "Mars probe", manned orbital stations "Salyut", "Mir" and it supplied several principal modules for ISS. It is used widely also for heavy satellites launches. The last RD-253 rocket engine was used on Proton-K rocket and launched on March 30, 2012.
Since the original development of the engine, several modifications were designed that weren't used in rockets. One of them was the RD-256 engine for which development stopped on experimental models. It wasn't used in flights and was designed for a cancelled vehicle. The modification marked RD-254 was supplied with extended nozzle for work in vacuum.
The modification RD-275 (14D14) appeared as the result of development in 1987-1993 years with the purpose to achieve a more powerful version of the engine. Its 7.7% higher thrust was reached by raising pressure in the combustion chamber and enabled to raise payload mass to geostationary orbit (GEO) up to more than 6,000 kg (13,000 lb). The successful maiden flight of a Proton rocket with the new engine was completed in 1995.
Energomash started the development of next more powerful version of engine in 2001. It has 5.2% higher thrust and has the designation 14D14M (RD-275M). It was designed to allow the rocket to deliver 150 kg (330 lb) more payload to GEO.
In the period from 2002 to 2003 years some experimental work was completed with this version of the engine. It included four test firings of three experimental RD-275M with a total time of 735 s. In the middle of 2005 this engine went into production by government commission. First launch of Proton-M with 14D14M engines is conducted July 7, 2007.
The final version RD-275M is sometimes designated as RD-276 but through 2009 the name RD-275M (14D14M) was more common. Some sources[which?] points out the cost of production per engine as much as 1.5 million USD and sometimes calls some lower figures around 1 million USD per unit.
During the years there have been many versions of this engine:
|Engine Type||Liquid propellant rocket engine using the oxidizer rich staged combustion cycle and burning N2O4/UDMH as propellant with an O/F ratio of 2.67|
|Combustion Chamber Pressure||14.7 MPa (2,130 psi)||14.7 MPa (2,130 psi)||14.7 MPa (2,130 psi)||14.7 MPa (2,130 psi)||14.7 MPa (2,130 psi)||16.9 MPa (2,450 psi)||14.7 MPa (2,130 psi)||15.7 MPa (2,280 psi)||16.5 MPa (2,390 psi)|
|Thrust (Vacuum)||1,074 kN (241,000 lbf)||1,120 kN (250,000 lbf)||1,634 kN (367,000 lbf)||1,700 kN (380,000 lbf)||1,635 kN (368,000 lbf)||1,870 kN (420,000 lbf)||1,720 kN (390,000 lbf)||1,750 kN (390,000 lbf)||1,832 kN (412,000 lbf)|
|Thrust (Sea Level)||947 kN (213,000 lbf)||N/A||1,471 kN (331,000 lbf)||N/A||1,474 kN (331,000 lbf)||1,720 kN (390,000 lbf)||N/A||1,590 kN (360,000 lbf)||1,671 kN (376,000 lbf)|
|Specific Impulse (Vacuum)||306 s (3.00 km/s)||318 s (3.12 km/s)||302 s (2.96 km/s)||314 s (3.08 km/s)||316 s (3.10 km/s)||317 s (3.11 km/s)||328 s (3.22 km/s)||316 s (3.10 km/s)||315.8 s (3.097 km/s)|
|Specific Impulse (Sea Level)||270 s (2.6 km/s)||N/A||272 s (2.67 km/s)||N/A||285 s (2.79 km/s)||290 s (2.8 km/s)||N/A||287 s (2.81 km/s)||288 s (2.82 km/s)|
|Height||2,600 mm (100 in)||4,200 mm (170 in)||3,470 mm (137 in)||5,050 mm (199 in)||3,000 mm (120 in)||2,700 mm (110 in)||4,000 mm (160 in)||3,050 mm (120 in)||3,050 mm (120 in)|
|Diameter||1,300 mm (51 in)||2,400 mm (94 in)||1,460 mm (57 in)||2,530 mm (100 in)||1,500 mm (59 in)||1,490 mm (59 in)||2,600 mm (100 in)||1,500 mm (59 in)||1,500 mm (59 in)|
|Intended Use||N-1 first stage||N-1 second stage||N-1 first stage||N-1 second stage||Proton (8K62) first stage||R-36M (15?14) first stage||UR-700 third stage, Proton and N-1 second stages||Proton-M first stage||Proton-M first stage|
|Status||Project (Abandoned)||Project (Abandoned)||Project (Abandoned)||Project (Abandoned)||Retired||Project (Abandoned)||Project (Abandoned)||Retired||In Production|
|References||Unless otherwise noted: |