R-13 turbojet engine. 1966 year.
The R-13 turbojet engine is a direct development of the R-11 engine, which was commonly used in MiG-21 aircraft. The engine was modernized under the supervision of S. Gawryłów. The aim of the modernization was to reduce fuel consumption, increase thrust and, above all, improve overall parameters.
The high pressure shaft was rebuilt. The high pressure compressor was converted from a 3-stage to a 5-stage one. The combustion chamber was rebuilt. Afterburner has been changed. Titanium was used on a larger scale. These changes made it easier to restart the engine when flying at high altitude.
The R-13 engine was adopted for service in 1966.
The R-13 engine was widely used in MiG-21 MF, MiG-21 SM, MiG-21 SMT, MiG-21 US, Su-15 T, Su-15 TM aircraft. In Poland, R-13 engines were used in MiG-21 MF and MiG-21 US aircraft.
Basic data of the R-13 engine:
The engine is single-flow, two-shaft, designed for supersonic flights (up to Ma 2.5). The maximum thrust without afterburning is 39.90 kN (4,068 kG). The maximum thrust with afterburning is 63.70 kN (6 495 kG). The afterburner increases engine thrust by 59.6%. Length 4.61 m. Diameter 0.967 m. Engine weight 1,210 kg.
Written by Karol Placha Hetman