Tumansky R-25

Tumansky R-25 is a turbojet engine, which is seen as the ultimate development of Tumansky R-11. It was designed under the leadership of Sergei Alekseevich Gavrilov.

Background

The Tumansky R-25 was designed as a replacement for Tumansky R-13 in MiG-21 fighters. R-25 is a two-spool axial-flow turbojet featuring a new compressor with increased overall pressure ratio and airflow, variable two-stage afterburner, and greater use of titanium.

The R-25 jet engine's specialty was the addition of a second fuel pump in the afterburning stage. Activating this "CSR" booster feature allows the engine to develop 96,8kN of thrust under 4000 meters of altitude. The limit of operation is 1 minute for dogfight practice and 3 minute for actual wartime emergency, as further use causes the engine to overheat and potentially explode. Use of CSR requires engine take-out inspection upon landing and every minute of its use counts as one full hour of engine runtime on the logbook.

This further shortens the already limited cycle time of soviet made engines between industrial-level overhauls and adds great cost, but the extreme thrust of CSR allowed to the MiG-21bis to reach better than 1:1 thrust-to-weight ratio for dogfight and outclimb the F-16. Yet, the older generation plane did not possess the advanced electronics suite and missiles of its rivals and its only success was a syrian MiG-21bis damaging an F-15A Eagle during the 1982 war.

The R-25 engine was used on MiG-21bis and Sukhoi Su-15bis. A total of 3,200 R-25 were built between 1971 and 1975. The engine was also built under license by HAL in India for their fleet of MiG-21bis.

pecifications (R-25-300)

jetspecs

type=Afterburning turbojet
length=4,615 mm (181.7 in)
diameter=1,191 mm (46.9 in)
weight=1,212 kg (2,670 lb)
compressor=Two-spool axial compressor
combustion=
turbine=
fueltype=
oilsystem=
power=
thrust=
*55 kN (12,370 lb) [ [http://www.globalsecurity.org/military/library/report/1985/SKJ.htm Globalsecurity.org: War in Afghanistan] ] military power
*68.5 kN (15,400 lbf) with afterburner
*96.8 kN for 3 minutes with boosted afterburner (CSR mode, altitude < 4000 meters)
compression=9.5:1
aircon=
turbinetemp=1,040 °C (1,904 °F)
fuelcon=
specfuelcon=
*93 kg/(h·kN) (0.91 lb/(h·lbf)) at idle
*98 kg/(h·kN) (0.96 lb/(h·lbf)) at maximum military power
*229 kg/(h·kN) (2.25 lb/(h·lbf)) with afterburner
power/weight=
thrust/weight=56.5 N/kg (5.8:1), 79.9 N/kg (8.1:1) with boosted afterburner