.jpg "Kuznetsov NK-12 turboprop engine © Konstantinos Panitsidis")
Photos from the personal collection of Konstantinos Panitsidis
Technical specifications 
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This engine is mainly intended for aircraft of the Tu-95 category (and for all versions of the Tu-142 and for civil airliners of the Tu-114 type), and has also been installed on aircraft such as the An-22 and the A-90 Orlyonok type wing-in-ground-effect, (ekranoplan).
The NK-12 (MV/MP) turboprop engine carries a large four-bladed contra-rotating propellers, AV-60K (P) or AV-60N variable pitch propeller, fixed speed, 5,6 m diameter. Propellers weight is 1.190 kg (front row 518 kg and rear row 637 kg).
The AV-60K (P) type variable pitch propeller has a total of eight propeller (the front row is equipped with four propeller and the rear row has another four propeller), with a rotation speed of 736 rpm, which counter-rotate against each other (the front row - rotates in the positive direction and the back row - rotates in the opposite direction). Profile of duralumin propeller NACA-16.
The engine has an independent oil tank with a total capacity of 135 liters. Apart from this, the engine is made up of other systems such as: two GSR-1800M DC generators, SGO-30U AC generator, AK-150NK air compressor, KTA-14N fuel control device, fuel pumps and other systems. The propulsion system is started by the airport's 27V generators or by a type TS-12M turbine starter.
The aviation fuel it uses is kerosene type T-1, T-2 or TS-1.
TECHNICAL SPECIFICATIONS
| Turboprop engine | NK-12 | NK-12M |
| Fuel | T-1, T-2, TS-1 | T-1, T-2, TS-1 |
| Oil | - | - |
| Propeller shaft power, take-off power rating | 12.500 h.p. | 15.000 h.p. |
| Propeller shaft power, cruise power (H=11000 m, Mf=0,68) | 6.500 h.p. | 6.500 h.p. |
| Specific fuel consumption, take-off power rating | 0,225 kg/h.p.*h | - |
| Specific fuel consumption, cruise power | 0,165 kg/h.p.*h | 0,158 kg/h.p.*h |
| Pressure ratio, take-take-off power rating | 9,5 | 9,5 |
| Rotation frequency | 8300 rpm | - |
| Temperature of the gas at the turbine intake, take-off power rating | 1.150 K | 1.150 K |
| Air flow rate, take-off power ratingς | - | - |
| Compressor rotation frequency low-pressure, take-off power rating | - | - |
| Weight (without propellers) | 2900 kg | 2900 kg |
| Propeller diameter | 5600 mm | 5600 mm |
| Engine diameter | 1005 mm | 1005 mm |
| Lenght | 6000 mm | 6000 mm |
| Service life limit (assigned operating time) | 150 h | 300 h |
| Overhaul operation time (TBO) | - | - |
