In numbers Through the lens Video
The engine is a single-circuit, single-spool design. It includes a 14-stage axial compressor with ten inlet rotary guide vanes, a tubular-annular combustion chamber with 12 flame tubes and centrifugal nozzles, and a three-stage turbine. The first stage of the turbine is air-cooled, which increases the service life of the blades and nozzle assemblies by reducing wear at high temperatures.
The engine is equipped with a straight-through afterburner, which consists of a front device, an afterburner pipe and an all-mode supersonic Laval nozzle.
Engine operating modes are controlled by a multifunctional hydromechanical system. The engine is started start using a turbo starter.
Since 1967, the engine has been installed on the Su-17 fighter-bomber and the Su-24 frontline bomber. The AL-21F aircraft gas turbine engine remains in service today.
Technical specifications
| DESIGNER | Lyulka |
| COUNTRY | Russia |
| TYPE |
Afterburning turbojet
|
| Installed On (aerial means) |
Su-17, Su-24
|
| Fuel | - |
| Oil | - |
| Maximum thrust take-off power rating | 8.157 kgf |
| Afterburner thrust | 11.216-11.736 kgf |
| Maximum thrust, cruise power | 6.240 kgf |
| Specific fuel consumption, cruise power | 0,725 kg/kgf*h |
| Specific fuel consumption, afterburner thrust rating | 1,901 kg/rgf*h |
| Pressure ratio, take-off power rating | 12,7 (14,75) |
| Bypass ratio | - |
| Temperature of the gas at the turbine intake, take-off power rating | 1.263 K |
| Air flow rate, take-off power rating | 88,5 kg/sec |
| Compressor rotation frequency low-pressure, take-off power rating | - |
| Compressor rotation frequency high-pressure, take-off power rating | - |
| OVERALL DIMENSIONS | |
| Diameter | 1030 mm |
| Height | - |
| Width | - |
| Length | 5340 mm |
| WEIGHT | |
| Engine weight | 1.580 kg |
| Specified service life | 1800 h |
| Overhaul operation time | 400 h |
Photos AL-21F Afterburning turbojet engine
Video
AL-21F Afterburning turbojet engine © Redstar.gr