Kuznetsov NK-12
The Kuznetsov NK-12 is a Soviet turboprop engine of the 1950s, designed by the Kuznetsov design bureau. The NK-12 drives two large four-bladed contra-rotating propellers, Template:Cvt diameter (NK-12MA), and Template:Cvt diameter (NK-12MV). It is the most powerful turboprop engine to enter service.
Design and development
The design that eventually became the NK-12 turboprop was developed after World War II by a team of Soviet scientists and imprisoned German engineers under Ferdinand Brandner, who had worked for Junkers previously; the design bureau was headed by chief engineer Nikolai D. Kuznetsov. Thus, the NK-12 design evolved from late-war German turboprop studies. This started with the postwar development of the wartime Jumo 022 turboprop design that was designed to develop Template:Cvt, weighing Template:Cvt. The effort continued with a Template:Cvt, weighing Template:Cvt, completed by 1947. Evolution to the TV-12 Template:Cvt engine required extensive use of new Soviet-developed alloys and was completed in 1951.
The NK-12 is the most powerful turboprop engine to enter service, ahead of the Europrop TP400 (in 2005). Another engine of similar size, the Pratt & Whitney T57 with Template:Cvt and Template:Cvt jet thrust, ran 3,100 hours before being cancelled in 1957.[1][2] The NK-12 powers the Tupolev Tu-95 bomber and its derivatives such as the Tu-142 maritime patrol aircraft and the Tupolev Tu-114 airliner (with NK-12MV), which still holds the title of the world's fastest propeller-driven aircraft despite being retired from service in 1991. 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".
The engine has a 14-stage axial-flow compressor, producing pressure ratios between 9:1 and 13:1 depending on altitude, with variable inlet guide vanes and blow-off valves for engine operability. The combustion system used is a cannular-type: each flame tube is centrally mounted on a downstream injector that ends in an annular secondary region. The contra-rotating propellers and compressor are driven by the five-stage axial turbine. Mass flow is 65 kg (143 lb) per second.[3]
Variants
Data from Alexandrov
- NK-12
- Template:Cvt, initial development model, used on the Tupolev Tu-95 and Tupolev Tu-116
- NK-12M
- Template:Cvt, used on the Tupolev Tu-114
- NK-12MV
- Template:Cvt,[4] Template:Cvt AV-60 propellers, used on the Tupolev Tu-95, Tupolev Tu-126, and Tupolev Tu-142
- NK-12MA
- Template:Cvt, Template:Cvt AV-90 propellers, used on the Antonov An-22
- NK-12MK
- Template:Cvt, Template:Cvt propellers, built with corrosion-resistant materials, used on the A-90 Orlyonok
- NK-12MP
- Template:Cvt,[5] modernized version used on the Tupolev Tu-95MS and Tupolev Tu-142M
- NK-12MPM
- Upgraded version of the NK-12MP that develops more power, produces half the vibration and is paired with the Aerosila AV-60T propeller; replaces the NK-12MP engine and AV-60K propeller on the Tupolev Tu-95MS[6]
Applications
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- A-90 Orlyonok
- Antonov An-22
- Tupolev Tu-95
- Tupolev Tu-114
- Tupolev Tu-116
- Tupolev Tu-126
- Tupolev Tu-142
Specifications (NK-12MV)
Data from Aircraft engines of the World 1970,[7] Civil Turboshaft/Turboprop Specifications[8]
General characteristics
- Type: Turboprop engine
- Length: Template:Cvt
- Diameter: Template:Cvt
- Dry weight: Template:Cvt
Components
- Compressor: 14-stage axial flow
- Combustors: 12 combustion chambers
- Turbine: 5-stage axial turbine
- Fuel type: Aviation kerosene such as JP-4 / Soviet spec. T-1 or T-2
- Oil system: Pressure spray at Template:Cvt
Performance
- Maximum power output: Template:Cvt (equivalent) / Template:Cvt + Template:Cvt at 9,250 rpm
- Overall pressure ratio: 13:1 at 9,250 rpm
- Air mass flow: Template:Cvt at 9,250 rpm
- Turbine inlet temperature: Template:Cvt
- Specific fuel consumption: Template:Cvt
- Power-to-weight ratio: Template:Cvt
See also
Related lists
References
External links
- ciad.ssau.ru - Image
- airventure.de - Image, finnish museum
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Template:Kuznetsov aeroengines
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