.jpg "Kuznetsov NK-8-2U turbofan engine © Konstantinos Panitsidis")
Photo from the personal collection of Konstantinos Panitsidis
Technical specifications 
Photos 
Video
The NK-8-2U turbofan engine is designed for installation on Tu-154A, Tu-154B and Tu-154S mainline jet aircraft. The NK-8-2U turbofan engine is basically a modified engine with increased thrust up to 10,500 kgf, based on the NK-8-2. Engine production has been imposed since 1972. In total, more than 2500 units were produced.
The NK-8-2U power plant is a turbofan, two-rotor, gas turbine engine with a mixture of air and gas flows, a thrust reverser cascade vanes and a common jet nozzle.
Turbofan engine NK-8-2U, Left side view (aircraft Tu-154B)
The NK-8-2U turbofan engine consists of:
- inlet guide vanes (IGV)
- two rotor, nine-stage axial compressor
- middle bearing
- annular combustion chamber
- two rotor three-stage axial turbine
- shells and mating ring
- reversing device
- exhaust nozzle (jet nozzle)
- units that provide and maintain the operation of aircraft engine systems.
Turbofan engine NK-8-2U, Right side view (aircraft Tu-154B).
TECHNICAL SPECIFICATIONS
| DESIGNER | OKB-276 N.D. Kuznetsov |
| COUNTRY | Russia (USSR) |
| TYPE OF ENGINE | Turbofan engine |
| Aircraft powered by the engine | Tu-154A (B and S) |
| Fuel | T-1, TS-1, T-7 |
| Oil | MK-8, MK-8P and synthetic oil VNII-IP-50-1-4F |
| Max thrust take-off power rating (H=0, V=0, ISA) | 10.500 kgf |
| Negative thrust in the mode not higher than the nominal (H=0, V=0, ISA) | 3600+150 kgf |
| Acceleration capability time | 8-10 s |
| Specific fuel consumption, take-off power rating | 0,580 kg/kgf.*h |
| Max thrust, cruise power (H=11.000 m, M=0,8) | 2.200 kgf |
| Specific fuel consumption, cruise power | 0,766 kg/kgf.*h |
| Compressor | |
| - the number of stage of | |
| a) low pressure compressor | 4 |
| b) high pressure compressor | |
| Pressure ratio, take-off power rating | 10,8 |
| Bypass ratio, take-off power rating | 1,05 |
| Combustion chamber | Annular type |
| Temperature of the gas at the turbine intake, take-off power rating | 1.156 K |
| Air flow rate, take-off power rating | 228 kg/sec |
| Compressor rotation frequency low-pressure, take-off power rating | - |
| Compressor rotation frequency high-pressure, take-off power rating | - |
| Turbine | |
| - the number of stages of | 1 |
| b) low pressure turbine | 2 |
| Jet nozzle | Constant-geometry type with mixing chamber. |
| Thrust reverser | With rotating cascade |
| Mass of engine | 2350+2% kg (including thrust reverser) |
| OVERALL DIMENSIONS | |
| -length with reverser and nozzle | 5288 mm |
| -length with jet nozzle | 4762 mm |
| Maximum engine diameter | 1442 mm |
| Dry weight of the engine | 2100 kg ±2% |
| Dry weight of engine with reverser and nozzle | 2350 kg ±2% |
| Engine overhaul life | Set by bulletins |
| Specified service life | 19.000 h |
| Shelf life of preserved engine | 5 years |
PHOTOS NK-82U turbofan engine
VIDEO
NK-8-2U turbofan engine © Redstar.gr
