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{{Short description|1950s Soviet turboprop aircraft engine}}
{|{{Infobox Aircraft Begin
{|{{Infobox aircraft begin
| name = NK-12
| image = Kuznetsov NK-12M turboprop on Tu-95.jpg
|name= NK-12
|image= File:Kuznetsov NK-12M turboprop on Tu-95.jpg
| caption = NK-12M Turboprop engine on a Tu-95 at RIAT Fairford 1993
|caption= NK-12M Turboprop engine on a Tu-95 at RIAT Fairford 1993
}}
}}
{{Infobox Aircraft Engine
{{Infobox aircraft engine
| type = [[Turboprop]]
|type= [[Turboprop]]
| national origin = [[Soviet Union]]
|national origin= [[Soviet Union]]
| manufacturer = [[Kuznetsov Design Bureau]]
|manufacturer= [[Kuznetsov Design Bureau]]
| first run =
|first run= October 1952
| major applications = [[Antonov An-22]] <br> [[Tupolev Tu-95]] <br> [[Tupolev Tu-114]]
|major applications= [[Antonov An-22]] <br> [[Tupolev Tu-95]] <br> [[Tupolev Tu-114]] <br> [[Tupolev Tu-142]]
| number built =
|number built=
⚫
|developed from=
| program cost =
⚫
|variants with their own articles=
| unit cost =
| developed from =
|developed into=
⚫
| variants with their own articles =
⚫
| developed into =
}}
}}
|}
|}
[[File:Энгельс Ту-95МС 23 фото 2.jpg|The exhaust ports of a NK-12 in an outboard nacelle on a TU-95|300px|thumb]]
[[File:Энгельс Ту-95МС 23 фото 2.jpg|The exhaust ports of a NK-12 in an outboard nacelle on a Tu-95|thumb]]
⚫
[[File:Antonov An-22A on the MAKS-2009 (04).jpg|thumb|300px|A pair of Kuznetsov NK-12MAs installed on an [[Antonov An-22]]]]


The '''Kuznetsov NK-12''' is a [[Soviet Union|Soviet]] [[turboprop]] engine of the 1950s, designed by the [[Kuznetsov Design Bureau|Kuznetsov]] [[OKB|design bureau]]. It drives two large four-bladed (eight blades per engine) [[contra-rotating propellers]], 5.6 m (18&nbsp;ft 4.5 in) in diameter, and 6.2 m (20&nbsp;ft 4.1 in) in the NK-12MA and NK-12MV. It is the most powerful turboprop engine to enter service.
The '''Kuznetsov NK-12''' is a [[Soviet Union|Soviet]] [[turboprop]] engine of the 1950s, designed by the [[Kuznetsov Design Bureau|Kuznetsov design bureau]]. The NK-12 drives two large four-bladed [[contra-rotating propellers]], {{cvt|5.6|m}} diameter (NK-12MA), and {{cvt|6.2|m}} diameter (NK-12MV). It is the most powerful turboprop engine to enter service.


==Design and development==
==Design and development==


The design that eventually became the NK-12 turboprop was developed after [[World War II]] by a team of Russian scientists and deported 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 [[Junkers Jumo 022|Jumo 022]] turboprop design that developed 6000 [[Horsepower#Shaft horsepower|eshp]] in a 3000&nbsp;kg (6,600 lb) engine. The effort continued with a 5000 ehp engine that weighed in at 1700&nbsp;kg (3,740 lb), 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.<ref>[http://www.janes.com/articles/Janes-Aero-Engines/Kuznetsov-NK-12-Russian-Federation.html Kuznetsov NK-12 (Russian Federation) - Jane's Aero-Engines<!-- Bot generated title -->]</ref>
The design that eventually became the NK-12 turboprop was developed after [[World War II]] by a team of Soviet scientists and deported 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 [[Junkers Jumo 022|Jumo 022]] turboprop design that was designed to develop {{cvt|6000|shp|lk=in}}, weighing {{cvt|3000|kg}}. The effort continued with a {{cvt|5000|shp}}, weighing {{cvt|1700|kg}}, completed by 1947. Evolution to the [[TV-12]] {{cvt|12000|shp}} engine required extensive use of new Soviet-developed alloys and was completed in 1951.<!--dead link which will NOT be recoverable<ref>[http://www.janes.com/articles/Janes-Aero-Engines/Kuznetsov-NK-12-Russian-Federation.html Kuznetsov NK-12 (Russian Federation) - Jane's Aero-Engines]</ref>-->


The NK-12M developed 8,948&nbsp;kW (12,000 ehp), uprated in the NK-12MV to 11,033&nbsp;kW (14,795 ehp) and reaching 11,185&nbsp;kW (15,000 ehp) in the NK-12MA. The NK-12 remains the most powerful turboprop engine to enter service although the [[Progress D-27]] and [[Europrop TP400]] have come close to this (in 1982 and 2005 respectively). Another engine of similar size, the Pratt & Whitney T57 with 15,000 shp and 5,000 lb jet thrust, ran 3,100 hours before being cancelled in 1957.<ref>"The Engines of Pratt & Whitney A Technical History, Jack Connors, AIAA Inc., {{ISBN|978-1-60086-711-8}} p.294</ref><ref>"Advanced Engine Development at Pratt & Whitney", Dick Mulready, SAE INternational, {{ISBN|0-7680-0664-3}} p.20</ref> The NK-12 powers the [[Tupolev Tu-95]] [[bomber]] and its derivatives such as the [[Tupolev Tu-142|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]] "[[Ground effect vehicle|Ekranoplan]]".
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 {{cvt|15000|shp}} and {{cvt|5000|lbf|kN}} jet thrust, ran 3,100 hours before being cancelled in 1957.<ref name="Connors">{{cite book |last1=Connors |first1=J. |title=The engines of Pratt & Whitney : a technical history |date=2010 |publisher=American Institute of Aeronautics and Astronautics |isbn=978-1-60086-711-8 |page=294}}</ref><ref name="Mulready">{{cite book |last1=Mulready |first1=Dick |title=Advanced engine development at Pratt & Whitney : the inside story of eight special projects, 1946-1971 |date=2001 |publisher=Society of Automotive Engineers |isbn=9780768006643 |page=20}}</ref> The NK-12 powers the [[Tupolev Tu-95]] [[bomber]] and its derivatives such as the [[Tupolev Tu-142|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]] "[[Ground effect vehicle|Ekranoplan]]".


The engine has a 14-stage axial-flow compressor, producing compression 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&nbsp;kg (143&nbsp;lb) per second.<ref name=autogenerated1>[http://www.airpages.ru/eng/ru/troph3.shtml Creation of the TV-2 (NK-12) turboprop engine<!-- Bot generated title -->]</ref>
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&nbsp;kg (143&nbsp;lb) per second.<ref name="airpages">{{cite web |title=Creation of the TV-2 (NK-12) turboprop engine |url=http://www.airpages.ru/eng/ru/troph3.shtml |website=www.airpages.ru |accessdate=22 March 2019}}</ref>

==Variants==
[[File:NK-12MV engine.jpg|thumb|NК-12МV]]
Data from Alexandrov

;NK-12:{{cvt|9300|kW|hp|order=flip}}, initial development model, used on the [[Tupolev Tu-95]] and [[Tupolev Tu-116]]
;NK-12M:{{cvt|8950|kW|hp|order=flip}}, used on the [[Tupolev Tu-114]]
;NK-12MV:{{cvt|11033|kW|hp|order=flip}},<ref name="MV">{{cite encyclopedia |title=NK-12MV |url=http://www.uvauga-dvig.narod.ru/nk-12mv.pdf |website=Ulyanovsk Higher Aviation School of Civil Aviation |language=Russian |page=18 |series=Domestic Aerospace Engineering |access-date=August 21, 2019}}</ref> {{cvt|5.6|m|ftin cm in|adj=mid|diameter|0}} AV-60 propellers, used on the [[Tupolev Tu-95]], [[Tupolev Tu-126]], and [[Tupolev Tu-142]]
;NK-12MA:{{cvt|11186|kW|hp|order=flip}}, {{cvt|6.2|m|ftin cm in|adj=mid|diameter|0}} AV-90 propellers, used on the [[Antonov An-22]]
;NK-12MK:{{cvt|11033|kW|hp|order=flip}}, {{cvt|5.6|m|ftin cm in|adj=mid|diameter|0}} propellers, built with corrosion-resistant materials, used on the [[A-90 Orlyonok]]
;NK-12MP:{{cvt|11033|kW|hp|order=flip}},<ref name="MP-MK">{{cite encyclopedia |title=NK-12MP, NK-12MK |url=http://www.uvauga-dvig.narod.ru/nk-12mp_12mk.pdf |website=Ulyanovsk Higher Aviation School of Civil Aviation |language=Russian |page=19 |series=Domestic Aerospace Engineering |access-date=August 21, 2019}}</ref> modernized version used on the [[Tupolev Tu-95]]MS and [[Tupolev Tu-142]]M
;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-95]]MS<ref name="AIN20181031">{{cite news |work=[[AINonline]] |title=More power for the mighty 'Bear' |url=https://www.ainonline.com/aviation-news/defense/2018-10-31/more-power-mighty-bear |date=31 October 2018 |given=Vladimir |surname=Karnozov |department=Defense}}</ref>


==Applications==
==Applications==
⚫
[[File:Antonov An-22A on the MAKS-2009 (04).jpg|thumb|A pair of Kuznetsov NK-12MAs installed on an [[Antonov An-22]]]]
* [[A-90 Orlyonok]]
* [[A-90 Orlyonok]]
* [[Antonov An-22]]
* [[Antonov An-22]]
Line 40: Line 51:
* [[Tupolev Tu-142]]
* [[Tupolev Tu-142]]


==Specifications==
==Specifications (NK-12MV)==
{{jetspecs
{{jetspecs
<!-- If you do not understand how to use this template, please ask at [[Wikipedia talk:WikiProject Aircraft]] -->
<!-- If you do not understand how to use this template, please ask at [[Wikipedia talk:WikiProject Aircraft]] -->
<!-- Please include units where appropriate (main comes first, alt in parentheses). If data are missing, leave the parameter blank (do not delete it). For additional lines, end your alt units with )</li> and start a new, fully-formatted line with <li> -->
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| ref = Aircraft engines of the World 1970,<ref name=Wilkinson70>{{cite book |last=Wilkinson |first=Paul H. |title=Aircraft engines of the World 1970 |year=1970 |publisher=Paul H. Wilkinson|location=London |edition=22nd |page=221}}</ref> Civil Turboshaft/Turboprop Specifications<ref>{{Cite web |url=http://www.jet-engine.net/civtsspec.html |title=Civil Turboshaft/Turboprop Specifications |access-date=2011-04-22 |archive-date=2017-07-29 |archive-url=https://web.archive.org/web/20170729043725/http://www.jet-engine.net/civtsspec.html |url-status=dead }}</ref>
| ref =
| type = turboprop
| type = [[Turboprop]] [[Aircraft engine|engine]]
| length = 4.8 m<ref name=autogenerated1 /> (199 ins.)
| length = {{cvt|6|m|ft}}
| diameter = 1.2 m<ref name=autogenerated1 /> (47 ins.)
| diameter = {{cvt|1150|mm|in}}
| weight = 2,900 kg (6393 lbs), for NK-12MV
| weight = {{cvt|2900|kg|lb}}
| compressor = Axial flow, 14 stages<ref name=autogenerated1 />
| compressor = 14-stage [[Axial compressor|axial flow]]
| combustion =
| combustion = 12 combustion chambers
| turbine = 5 stages<ref name=autogenerated1 />
| turbine = 5-stage [[axial turbine]]
| fueltype = [[Aviation fuel|Aviation kerosene]] such as [[JP-4]] / Soviet spec. T-1 or T-2
| fueltype =
| oilsystem =
| oilsystem = Pressure spray at {{cvt|85|psi|bar|order=flip}}
| power = {{cvt|15000|shp|kW|order=flip}} (equivalent) / {{cvt|14750|shp|order=flip}} + {{cvt|625|lbf|kN|order=flip}} at 9,250 rpm
| power = 11,033 kW (14,795 ehp), for NK-12MV
| thrust =
| thrust =
| compression = 9.5<ref name=autogenerated1 />
| compression = 13:1 at 9,250 rpm
| bypass =
| bypass =
| aircon =
| aircon = {{cvt|65|kg/s|lb/s}} at 9,250 [[Revolutions per minute|rpm]]
| turbinetemp = 1250 K<ref name=autogenerated1 />
| turbinetemp = {{cvt|1250|K|C}}
| fuelcon =
| fuelcon =
| specfuelcon = {{cvt|0.360|lb/hph|kg/kWh|order=flip}}
| specfuelcon = 0.360 lb/shp-hr <ref>[http://www.jet-engine.net/civtsspec.html Civil Turboshaft/Turboprop Specifications<!-- Bot generated title -->]</ref> 0.219 kg/kW-hr for NK-12MA and NK-12MV
| power/weight = 3.7 kW/kg (2.3 hp/lb), for NK-12MV
| power/weight = {{cvt|3.7|kW/kg|hp/lb}}
| thrust/weight =
| thrust/weight =
}}
}}
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* [https://web.archive.org/web/20110813145414/http://ciad.ssau.ru/work-images/nk-12_big.jpg ciad.ssau.ru - Image]
* [https://web.archive.org/web/20110813145414/http://ciad.ssau.ru/work-images/nk-12_big.jpg ciad.ssau.ru - Image]
* [http://www.airventure.de/tipps_zentralfinnisches_luftfahrtmuseum/Museum_Finnland_Kuznetsov_Triebwerk.jpg airventure.de - Image, finnish museum]
* [http://www.airventure.de/tipps_zentralfinnisches_luftfahrtmuseum/Museum_Finnland_Kuznetsov_Triebwerk.jpg airventure.de - Image, finnish museum]
* {{cite web |url=http://aerosila.ru/en/products/vozdushnye-vinty-ivintoventilyatory-dlya-samoletov/vintoventilyatory-klass-tyagi-10000-kgs |title=Propfans: Thrust class > 10000 kgf: Technical characteristics |website=Aerosila |archive-date=October 15, 2017 |url-status=live |archive-url=https://web.archive.org/web/20171015225141/http://aerosila.ru/en/products/vozdushnye-vinty-ivintoventilyatory-dlya-samoletov/vintoventilyatory-klass-tyagi-10000-kgs}}


{{Kuznetsov aeroengines}}
{{Kuznetsov aeroengines}}
{{aeroengine-specs}}


[[Category:Kuznetsov aircraft engines|NK-12]]
[[Category:Kuznetsov aircraft engines|NK-12]]
[[Category:Turboprop engines 1950–1959]]
[[Category:1950s turboprop engines]]

Latest revision as of 18:34, 6 August 2024

NK-12
NK-12M Turboprop engine on a Tu-95 at RIAT Fairford 1993
Type Turboprop
National origin Soviet Union
Manufacturer Kuznetsov Design Bureau
First run October 1952
Major applications Antonov An-22
Tupolev Tu-95
Tupolev Tu-114
Tupolev Tu-142
The exhaust ports of a NK-12 in an outboard nacelle on a Tu-95

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, 5.6 m (18 ft) diameter (NK-12MA), and 6.2 m (20 ft) diameter (NK-12MV). It is the most powerful turboprop engine to enter service.

Design and development

[edit]

The design that eventually became the NK-12 turboprop was developed after World War II by a team of Soviet scientists and deported 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 6,000 shp (4,500 kW), weighing 3,000 kg (6,600 lb). The effort continued with a 5,000 shp (3,700 kW), weighing 1,700 kg (3,700 lb), completed by 1947. Evolution to the TV-12 12,000 shp (8,900 kW) 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 15,000 shp (11,000 kW) and 5,000 lbf (22 kN) 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

[edit]
NК-12МV

Data from Alexandrov

NK-12
12,500 hp (9,300 kW), initial development model, used on the Tupolev Tu-95 and Tupolev Tu-116
NK-12M
12,000 hp (8,950 kW), used on the Tupolev Tu-114
NK-12MV
14,795 hp (11,033 kW),[4] 5.6 m diameter (18 ft 4 in; 560 cm; 220 in) AV-60 propellers, used on the Tupolev Tu-95, Tupolev Tu-126, and Tupolev Tu-142
NK-12MA
15,001 hp (11,186 kW), 6.2 m diameter (20 ft 4 in; 620 cm; 244 in) AV-90 propellers, used on the Antonov An-22
NK-12MK
14,795 hp (11,033 kW), 5.6 m diameter (18 ft 4 in; 560 cm; 220 in) propellers, built with corrosion-resistant materials, used on the A-90 Orlyonok
NK-12MP
14,795 hp (11,033 kW),[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

[edit]
A pair of Kuznetsov NK-12MAs installed on an Antonov An-22

Specifications (NK-12MV)

[edit]

Data from Aircraft engines of the World 1970,[7] Civil Turboshaft/Turboprop Specifications[8]

General characteristics

  • Type: Turboprop engine
  • Length: 6 m (20 ft)
  • Diameter: 1,150 mm (45 in)
  • Dry weight: 2,900 kg (6,400 lb)

Components

Performance

  • Maximum power output: 11,000 kW (15,000 shp) (equivalent) / 11,000 kW (14,750 shp) + 2.78 kN (625 lbf) at 9,250 rpm
  • Overall pressure ratio: 13:1 at 9,250 rpm
  • Air mass flow: 65 kg/s (140 lb/s) at 9,250 rpm
  • Turbine inlet temperature: 1,250 K (980 °C)
  • Specific fuel consumption: 0.219 kg/kWh (0.360 lb/(hp⋅h))
  • Power-to-weight ratio: 3.7 kW/kg (2.3 hp/lb)

See also

[edit]

Related lists

References

[edit]
  1. ^ Connors, J. (2010). The engines of Pratt & Whitney : a technical history. American Institute of Aeronautics and Astronautics. p. 294. ISBN 978-1-60086-711-8.
  2. ^ Mulready, Dick (2001). Advanced engine development at Pratt & Whitney : the inside story of eight special projects, 1946-1971. Society of Automotive Engineers. p. 20. ISBN 9780768006643.
  3. ^ "Creation of the TV-2 (NK-12) turboprop engine". www.airpages.ru. Retrieved 22 March 2019.
  4. ^ NK-12MV (PDF). Domestic Aerospace Engineering (in Russian). p. 18. Retrieved August 21, 2019. {{cite encyclopedia}}: |website= ignored (help)
  5. ^ NK-12MP, NK-12MK (PDF). Domestic Aerospace Engineering (in Russian). p. 19. Retrieved August 21, 2019. {{cite encyclopedia}}: |website= ignored (help)
  6. ^ Karnozov, Vladimir (31 October 2018). "More power for the mighty 'Bear'". Defense. AINonline.
  7. ^ Wilkinson, Paul H. (1970). Aircraft engines of the World 1970 (22nd ed.). London: Paul H. Wilkinson. p. 221.
  8. ^ "Civil Turboshaft/Turboprop Specifications". Archived from the original on 2017-07-29. Retrieved 2011-04-22.
[edit]
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