Tumanski R-15
The Tumanski R-15 is a Soviet single-shaft, single-flow air jet engine . It was developed by OKB Tumanski in the late 1950s .
development
The R-15-300 was the OKB-300 Tumanski from 1959 for the Tu-121 - cruise missile developed. This should fly about 4000 km at high altitude with Mach 2.5. Accordingly, the engine was optimized for maximum altitude and designed as a consumable material with an extremely short service life of 50 operating hours.
When a new interceptor, the Je-150, was designed, it was decided to develop its engines from the R-15. An increased service life and usability in the partial load range and for take-off and landing were added as new requirements.
power
Without the addition of an afterburner, the R-15F-300 developed 67.03 kN, with an afterburner 100.5 kN of thrust. The single-jet Je-152-1 thus achieved Mach 2.5. The twin - engine Mikojan-Gurewitsch MiG-25 with its R-15B-300 (73.5 kN without, 110 kN with afterburner) was able to reach Mach 3.2, but was in peacetime to Mach 2.8 limited to avoid damage to the engines. The specific fuel consumption was very high, especially at low altitudes.
variants
- KR-15-300 or R-15K-300 : Original version for the Tu-121 cruise missile and the Tupolev Tu-123 “Jastreb” drone .
- R-15B-300 : electronic control (first Soviet engine with electronic control), improvements to increase the service life (increased from 150 to 750 h in the course of series production). Original engine of the MiG-25.
- R-15BD-300 : improved and more powerful version for the MiG-25PD.
- R-15BF2-300 : again more powerful version for the Je-155M (prototype of the MiG-25M). No series production; the MiG-31 developed from the MiG-25M received 2 Solowjow D-30 F6 as series engines.
use
Series aircraft
Prototypes
Technical specifications
| R-15B-300 | R-15BF2-300 | |
|---|---|---|
| Length (mm) | 6264 6655 (MiG-25RB) |
|
| Diameter (mm) | 1640 | |
| Dry matter (kg) | 2706 2772 (MiG-25, MiG-25RB) |
|
| compressor | five-stage axial compressor | |
| Gas turbine | single-stage high pressure stage | |
| Thrust (kN) | 73.5 | 98 |
| 110 (afterburner) | 142 (afterburner) | |
| compression | 4.75: 1 | 4.95: 1 |
| Combustion chamber inlet temperature (° C) | 942 | |
| Combustion chamber outlet temperature | 820 | |
| Specific fuel consumption (kg / [h · kN]) | 127 (idle) 275 (with afterburner) |
|
Individual evidence
Web links
- R-15. In: leteckemotory.cz. Retrieved September 1, 2017 (Czech).
- Турбореактивный двигатель с форсажной камерой Р-15. In: Airwar.ru. Retrieved September 1, 2017 (Russian).