Kuznetsov NK-12

The Kuznetsov NK -12 is a turboprop engine of the Russian producer Kuznetsov. The development started in 1952, and the NK -12 with a maximum of 15,000 horsepower to this day the most powerful turboprop engine ever to be produced in series.

Is a Einwellentriebwerk which drives via a double planetary gear, two coaxial counter-rotating propellers. It was developed in Kuibyshev in 1953 by a group of engineers from the former Junkers works under the leadership of the Austrian Ferdinand Brandner. The technicians had been spent together with numerous other aviation specialists in the Soviet Union in 1946.

After the group had developed there, among other things, the engine 022, which was later than Kuznetsov NK -4 come in 4,000 and 5,000 -horsepower versions of widely used, we saw a need for a far more powerful engine. From November 1952 Tu- 95 flight tests with the double engine 2TW -2F were carried out with the first prototype of the Tupolev, consisting of two coupled NK -4. After the crash of the machine due to gearbox problems, it was decided to develop a Einturbinentriebwerks with the type designation NK -12 and first 12,000 hp. The first runs on the test found in 1953, which first flight in 1955 with the second prototype of the Tu -95.

Except in the case of the Tu- 95, the engine came in its various variants at the Antonov An-22 and Tupolev Tu -114 is used. Also great for Ekranoplane served the engine as the drive. It is still the most powerful turboprop engine ever to be produced in series.

Variants

  • TW -12: 8,000 kW ( 10,880 hp)
  • NK -12: 8,948 kW ( 12,170 hp)
  • NK -12M: 11,185 kW ( 15,211 hp)
  • NK - 12MA: 11,185 kW ( 15,211 hp)
  • NK - 12MW: 11,033 kW ( 15,005 hp)
  • NK - 12MK: 9,900 kW ( 13,464 hp)
  • NK - 12MP: 11,030 kW ( 15,000 hp)

Specifications (NK -12)

  • Turbine speed: 8300 min-1
  • Turbine inlet temperature: 1,150 K
  • Weight (without propeller ): 2900 kg
  • MTBO: 100 h
  • Power: 9,188 kW (12,500 hp)

Specifications (NK - 12MP )

  • Compressors: axial 14 -stage
  • Turbine: axial 5-stage
  • Air flow: 65 kg / s
  • Turbine speed: 8300 min-1
  • Propeller speed: 750 min-1
  • Compression: 9,7:1
  • Turbine inlet temperature: about 1150 K
  • Weight: 3500 kg
  • MTBO: 5,000 h
  • Length: 4,837 mm
  • Diameter: 1,620 mm
Samara, Russia Europrop TP400
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