RD-191

RD-191 engines for first stage of “Angara” launch-vehicle family

The development of RD-191 engine was begun at the end of 1998. This engine with afterburning of oxidizer-rich gas is intended for the family of the domestic “Angara” and “Baikal” launch-vehicles. The design of this engine also is based on a design of RD-170/171 engines. The RD-191 engine represents single chamber LPRE with vertically located TPU. Within 1999 the design documentation was issued, in 2000 the autonomous development of RD-191 engine units was started, the preparation of production is completed. In May 2001 the first development engine RD-191 was assembled. The first fire test of RD-191 engine was conducted

Main parameters of RD-191 engine

Liquid propellant rocket engine with afterburning of oxidizer-rich gas

Propellant liquid oxygen + kerosene

Engine modifications	RD-191
Thrust, sea level / vacuum, tf	196 / 213
Specific impulse, sea level / vacuum, sec	310,7 / 337
Combustion chamber pressure, kgf/cm²	263,4
Weight, dry, kg	2200
Overall dimensions, height / diameter, mm	4000 / 1450
Period of development	1999 -
Purpose	“Angara”

63 fire tests of the engine with common running time more than 11800 sec were conducted on 7.12.07. The maximum time of single test makes 450 sec. The results of engine tests have confirmed main parameters, foreseen in the engine specification. The development of the engine is made pursuant to the program of experimental development, which is foreseen the production of 10 engines for 100 fire tests. The basic principle of such program - small number of engines and large running time on each development engine with maximum quantity of measurements.