RD-253 engines for first stage of “Proton” launch-vehicle

The development of the RD-253 engine was begun in 1961. It became most powerful single chamber liquid propellant rocket engine at storable propellant components. The engine is made under the scheme with afterburning of oxidizer-rich gas. The maiden launch of the “Proton” launch-vehicle with RD-253 engines took place in July, 1965. The qualitative breakthrough in mastering of a high level of pressure and achievement of high values of specific impulse of thrust is accomplished thanks to RD-253. The RD-253 engine is one of the most reliable domestic rocket engines.

            Six RD-253 liquid propellant rocket engines reliably worked in a structure of a first stage of the “Proton” launch-vehicle providing successful flights of different spacecrafts as “Luna”, “Venera”, “Mars” and other, and also orbital space stations “Salut” and “Mir”, elements of International Space Station, heavy communication satellites.

            The serial production of these engines is conducting at a serial production plant in Perm under supervision of Kamskiy branch of NPO Energomash.

 Main parameters of the RD-253 engine family

Liquid propellant rocket engine with afterburning of oxidizer-rich gas

Propellant   nitrogen tetroxide + UDMH

The activities on RD-253 engine modification were conducted in 1987-1993. The RD-275 (14D14) index was assigned to new modification. The engine thrust was increased by 7,7 % due to increase a pressure in the combustion chamber, that allows to increase a payload mass on 600 kg. The maiden launch of the “Proton” launch-vehicle with RD-275 engines was conducted in October 1995.

Kamskiy branch in 2001 has began development of the 14D14M engine - forced (on 5,2 % thrust) modification of a serial production engine RD-275. Such thrust increase of the engine allows to increase payload mass put by rocket at stationary orbit for 150 kg.

In 2002-2003 the issue of design and manufacturing documentation on the engine 14D14M (RD-275M) was conducted, 4 fire tests 3 development engines 14Ä14Ì with operating time(running time) of 735 sec are held.

The program of interbranch tests of 3 14D14M engines was successfully completed in summer 2005. The serial production of new modified 14D14M engines is begun. First launch of “Proton-M” LV with 14D14M engines is conducted July 7^th, 2007.