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Tumansky R-25
From Wikipedia, the free encyclopedia
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.
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 afterburner, and greater use of titanium. The 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.
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)
Components
- Compressor: Two-spool axial compressor
Performance
- Thrust:
- 40.3 kN (9,060 lbf) military power
- 68.5 kN (15,400 lbf) with afterburner
- 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)
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