Tumansky R-25

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Tumanski R-25-300 MiG-21bis MG-116 Karhulan ilmailukerhon lentomuseo 1.JPG
Tumanski R-25-300 engine in Karhulan ilmailukerho Aviation Museum
Type Turbojet
Manufacturer Tumansky
First run 1971
Major applications Sukhoi Su-15
Mikoyan-Gurevich MiG-21
Number built 3,200
Developed from Tumansky R-11

The 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.

Design and development[edit]

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 the ЦР(чрезвычайный режим - emergency mode) booster feature allows the engine to develop 96.8 kilonewtons (21,800 lbf) of thrust under 4,000 metres (13,000 ft) of altitude. The limit of operation is 1 minute for dogfight practice and 3 minutes for an 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 the MiG-21bis to reach a 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 the MiG-21bis and the 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 its fleet of MiG-21bis.

Specifications (R-25-300)[edit]

General characteristics

  • Type: Afterburning turbojet
  • Length: 4,615 mm (181.7 in)
  • Diameter: 1,191 mm (46.9 in)
  • Dry weight: 1,212 kg (2,670 lb)



  • Maximum thrust:
  • 55 kilonewtons (12,000 lbf) [1] military power
  • 68.5 kilonewtons (15,400 lbf) with afterburner
  • 96.8 kilonewtons (21,800 lbf) for 3 minutes with boosted afterburner (CSR mode, altitude < 4,000 metres (13,000 ft))
  • Overall pressure ratio: 9.5:1
  • Turbine inlet temperature: 1,040 °C (1,904 °F)
  • Specific fuel consumption:
  • 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
  • Thrust-to-weight ratio: 56.5 N/kg (5.8:1), 79.9 N/kg (8.1:1) with boosted afterburner

See also[edit]

Related development
Related lists


External links[edit]