NK-25 Turbofan Engine Technology
The NK-25 three-stage bypass turbofan engine features turbine blade radial clearance active control and stator rings perforation for increased compressor stability. The rotor blades
and the nozzle vanes are cooled with vortex flows. The engine has an anti-surge protection
with automatic recovery of the initial operation mode. The engine control system is electronic.
The NK-25 engine is designed for the Tu-22M3E multirole aircraft.
D-30F6 Turbofan Engine
D-30F6 Turbofan Engine Technology. The D-30F6 engine features a two-shaft configuration with exhaust mixing from both ducts. The engine consists of seven modules. It has a low-pressure five-stage compressor, a high-pressure ten-stage compressor and a cannular combustion chamber. The low- and high-pressure turbines are two-staged. The nozzle vanes and highpressure turbine rotor blades are cooled. The afterburner houses the exhaust mixer and has four ring flame stabilisers. The multivane supersonic nozzle is cooled.
The engine design enables onboard parameter monitoring. Reliability of the engine is ensured by the protection, backup, and early malfunction detection systems. The electro-hydraulic engine control
system is backed up with the hydraulic system activated if the electronic one has failed to ensure flight safety and effective mission accomplishment.
The engine has unique altitude and airspeed performance, providing maximum airspeed of 3,000 km/h at altitude and 1,500 km/h near ground. The D-30F6 engine is designed to power the MiG-31E fighter/interceptor.
D-30F6 Turbofan Engine Specifications
Thrust, kgf:
max continuous (H=0, M=0, ISA) 9,500
full afterburner 15,500
Specific fuel consumption, kg/kgf/h:
max continuous (H=0, M=0) 0.20
full afterburner 1.90
Bypass ratio 0.57
Air consumption, kg/sec 150
Pressure ratio (total) 21.15
Gas temperature before the turbine, oK 1,640
Engine dry weight, kg 2,416
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