|NK-12M Turboprop engine on a Tu-95 at RIAT Fairford 1993|
|National origin||Soviet Union|
|Manufacturer||Kuznetsov Design Bureau|
|Major applications||Antonov An-22
The Kuznetsov NK-12 is a Soviet turboprop engine of the 1950s, designed by the Kuznetsov design bureau. It drives large eight-bladed (four per propeller) contra-rotating propellers 5.6 m (18 ft 4.5in) in diameter (6.2 m (20 ft 4.1in) in the NK-12MA and NK-12MV). It is the most powerful turboprop engine ever built.
Design and development
The design that eventually became the NK 12 turboprop was developed after World War II by a team of deported German engineers under Ferdinand Brandner, which had worked for Junkers previously. Thus, NK 12 design evolved from late war German turboprop studies. This started with the post-war development of the wartime Jumo 022 turboprop design that developed 6000 eshp in a 3000 kg engine. The effort continued with a 5000 ehp engine that weighed in at 1700 kg, completed by 1947. The evolution to the TV-12 12000 Ehp engine required extensive use of new Soviet-developed alloys and was completed in 1951.
The NK-12M developed 8,948 kW (12,000 ehp), uprated in the NK-12MV to 11,033 kW (14,795 ehp) and reaching 11,185 kW (15,000 ehp) in the NK-12MA. The NK-12 remains the most powerful turboprop engine ever built. Only recently the Progress D-27 and Europrop TP400 came somewhat close. It powered the Tupolev Tu-95 bomber and its descendants like the Tu-142 maritime patrol aircraft and the Tupolev Tu-114 airliner (with NK-12MV), which is still the world's fastest propeller-driven aircraft. It also powered the Antonov An-22 Antei (with NK-12MA), the world's largest aircraft at the time, and several types of amphibious assault craft, such as the A-90 Orlyonok "Ekranoplan" and the Zubr class LCAC.
The engine has a 14-stage axial-flow compressor, producing compression ratios between 9:1 to 13:1 depending on altitude, also controlled by variable inlet guide vanes and blow-off valves. The combustion system used is a cannular-type: each flame tube is centrally mounted on a down-stream injector that ends in an annular secondary region. The contra-rotating propellers and compressor are driven by the 5-stage axial turbine. Mass flow is 65 kg (143 lb) /sec.
- Maximum power output: 11,033 kW (14,795 ehp), for NK-12MV
- Overall pressure ratio: 9.5
- Turbine inlet temperature: 1250K
- Specific fuel consumption: 0.360 lb/shp-hr  0.219 kg/kW-hr for NK-12MA and NK-12MV
- Power-to-weight ratio: 3.7 kW/kg (2.3 hp/lb), for NK-12MV
- Related lists
|Wikimedia Commons has media related to Kuznetsov NK-12.|
|This aircraft engine article is missing some (or all) of its specifications. If you have a source, you can help Wikipedia by adding them.|