.jpg "R11F2-300 Turbojet engine © Konstantinos Panitsidis")
In numbers Through the lens Video
The engine was mass-produced between 1962 and 1975. By 1997, more than 20,000 engines of all variants had been manufactured.
Development of the AM-11 turbojet engine (also designated R11F-300) was initiated in 1953 at OKB-300 under the direction of A. A. Mikulin. Leadership of the program was later transferred to S. K. Tumansky.
The engine is a two-spool axial-flow turbojet and comprises the following principal assemblies:
Compressor - axial-flow type, consisting of:
- a three-stage low-pressure compressor (LPC);
- a three-stage high-pressure compressor (HPC).
Combustion system - tubular-annular combustion chamber.
Turbine - axial-flow type, consisting of:
- a single-stage high-pressure turbine (HPT);
- a single-stage low-pressure turbine (LPT).
Exhaust system - variable-area jet nozzle.
Both the low-pressure and high-pressure compressors incorporate three high-pressure supersonic (transonic-speed) stages. The engine is of a non-outrigger configuration, with all supports integrated into the main engine structure.
The engine operates on aviation kerosene grades T-1, TS-1, and RT. Serial production was carried out by JSC V.V. Chernyshev Moscow Machine-Building Enterprise.
Technical specifications
| DESIGNER | Open Society AESTC “Soyuz” (S.K. Tumansky) |
| COUNTRY | Russia |
| TYPE |
Turbojet engine (with afterburning)
|
| Installed On (aerial means) |
MiG-21PFM, MiG-21UM, MiG-21R, Su-15, MiG-21S, MiG-21M
|
| Fuel | T-1, T-2, TS-1, RT |
| Oil | MK-8 or MS-6 |
| Maximum thrust with afterburning, takeoff condition | 6.120 kgf |
| Maximum thrust, takeoff condition | 4.200 kgf |
| Specific fuel consumption with afterburning, take-off condition | 2,2 kg/kgf*h |
| Specific fuel consumption, take-off condition | 0,94 kg/kgf*h |
| Maximum thrust, cruise condition | - |
| Specific fuel consumption, cruise condition | - |
| Pressure ratio, take-off condition | 8,7 |
| Bypass ratio, take-off condition | - |
| Specific weight | 0,191 kg/kgf |
| Temperature of the gas at the turbine intake, take-off power rating | 1.175 K |
| Air flow rate, take-off power rating | 66 kg/sec |
| Compressor rotation frequency low-pressure, take-off power rating | - |
| Compressor rotation frequency high-pressure, take-off power rating | - |
| Maximum low-pressure rotor speed in afterburner mode (thrust 6.120 kgf) | 11159±50 rpm |
| Minimum low-pressure rotor speed in afterburner mode | 11159±50 rpm |
| Maximum low-pressure rotor speed without afterburner | 11159±50 rpm |
| Energy conversion efficiency, ηLPC | 0,82 |
| Energy conversion efficiency, ηHPC | 0,83 |
| Combustion efficiency of fuel, ηc | 0,97 |
| Combustor total pressure recovery coefficient, σcс | 0,94 |
| Energy conversion efficiency, ηHPR | 0,88 |
| Energy conversion efficiency, ηLPR | 0,89 |
| Nozzle velocity coefficient, φn | 0,97 |
| OVERALL DIMENSIONS | |
| Diameter | 825 mm |
| - largest | 906 mm |
| Height (including protruding components) | 1085 mm |
| Width | - |
| Length | 4600 mm |
| WEIGHT | |
| Engine weight | 1.088 kg |
| Specified service life | 1.500 h |
Photos R11F2-300 Afterburning turbojet engine
Video
R11F2-300 Afterburning turbojet engine © Redstar.gr