The NK 8 was a low bypass turbofan engine built by the Kuznetsov Design Bureau , in the 20,000 pound force lbf 90 kilonewton kN thrust class. It powered production models of the Ilyushin Il 62 and the Tupolev Tu 154 A and B models. External links http www.leteckemotory.cz motory nk 8 nk 8.php NK 8 on LeteckeMotory.cz NK 8 cs Kuznetsov aeroengines Aviation lists engine aircraft stub Category Low bypass turbofan engines Category Turbofan engines 1960 1969 Category Kuznetsov aircraft engines fr Kouznetsov NK 8 ru 8 ... more details
Unreferenced date March 2009 The Kuznetsov NK 25 is a turbofan engine used in the Tupolev Tu 22M strategic bomber. It can equal the NK 321 engine as one of the most powerful supersonic engines in service today. It is rated at 245 kN 50,000 lbf thrust. The three shaft engine we call the NK 25 was designed in the years 1972 1974. It was superior to many other engines because of its improved fuel economy. It is made by the Soviet Kuznetsov Design Bureau . External links http www.leteckemotory.cz motory nk 25 NK 25 on LeteckeMotory.cz czech Kuznetsov aeroengines Aviation lists DEFAULTSORT Kuznetsov Nk 25 Category Low bypass turbofan engines Category Turbofan engines 1960 1969 Category Kuznetsov aircraft engines fr Kouznetsov NK 25 it Kuznetsov NK 25 ru 25 ... more details
The Kuznetsov NK 144 is an afterburning turbofan engine made by the Soviet Kuznetsov Design Bureau . Used on the early models of the Tupolev Tu 144 supersonic aircraft, it was very inefficient and was replaced with the Kolesov RD 36 51 turbojet engine. Specifications NK 144 aeroengine specs Thrust kg 28,660 dry 38,580 wet Airflow 551 lb s Overall pressure ratio OPR 14.2 Bypass ratio BPR 0.60 Spools 2 2 Specific fuel consumption thrust SFC 1.81 lb lbf hour ref http www.tupolev.ru english Show.asp?SectionID 148&Page 2 PSC Tupolev TU 144 Bot generated title ref Data from ref http www.jet engine.net civtfspec.html Civil Turbojet Turbofan Specifications Bot generated title ref References reflist External links http www.leteckemotory.cz motory nk 144 NK 144 on LeteckeMotory.cz czech Kuznetsov aeroengines Aviation lists engine aircraft stub Category Low bypass turbofan engines Category Turbofan engines 1960 1969 Category Kuznetsov aircraft engines fr Kouznetsov NK 144 ja NK 144 ... more details
This article is a part of Wikipedia WikiProject Aircraft . Please see Wikipedia WikiProject Aircraft page content for recommended layout. Infobox Aircraft Begin name F107 WR19 image File Williams International F 107 USAF.JPG caption An F107 engine on display at the National Museum of the USAF Infobox Aircraft Engine type Turbofan national origin United States manufacturer Williams International first run 1970s major applications AGM 86 ALCM br BGM 109 Tomahawk number built program cost unit cost developed from developed into Williams F112 variants with their own articles The Williams F107 company designation WR19 is a small turbofan engine made by Williams International . The F107 was designed to power cruise missile s. It has been used as the powerplant for the AGM 86 ALCM , and BGM 109 Tomahawk , as well as the experimental Williams X Jet flying platform. Applications AGM 86 ALCM BGM 109 Tomahawk Kaman KSA 100 SAVER Williams X Jet Jet pack Bell Jet Flying Belt Bell Aerospace Flying Jet Belt Specifications jetspecs 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 ref type Turbofan length 1,262 mm diameter 305 mm weight 66.2 kg compressor Twin spool, axial, counter rotating combustion turbine fueltype oilsystem power thrust 2.7 kN for F107 WR 400 3.1 kN for F107 WR 402 compression bypass 1 1 aircon turbinetemp fuelcon specfuelcon 0.682 kg kg h ref http www.mzak.cz motory williams williams.php mzak.cz motory williams ref power weight thrust weight 4.6 1 See also Aircontent related Williams F112 similar engines lists List of aircraft engines see also References reflist Leyes, Richard A., and William A. Fleming, The History of North American Small Gas Turbine Aircraft Engines , Smith ... more details
no footnotes date March 2012 Julius Mackerle 18 June 1909 Jev ko , Moravia 11 September 1988 was a Czech inventor and automobile engineer. Life His father, Julius, owned brickworks firm in Jev ko and his brother Jaroslav Mackerle 1913 1964 was an architect, designer and amateur archeologist. Julius Mackerle was an inventor, automobile engineer and head designer of Tatra company Tatra Kop ivnice , a specialist on air cooled engines. He studied at Technical University in Brno where he constructed his first motorcar a two seater sportroadster with 1,000cc JAP motorcycle engine. He finished his studies in 1935. Initially he worked at koda Works koda Plze as a head of motor engine department and then he transferred to Prague branch of the koda Works koda company. In 1948 he started to work for Tatra company Tatra in Kop ivnice where he designed engines for Tatra trucks T 128 and 138. In 1949 under his leadership an engine for a racing Tatraplan T607 and T607 2 with ejector cooling system was developed. In the early 1950s Mackerle designed the concept for Tatra T603 V8 engine. In 1958 Mackerle worked as a director of engine design at stav pro v zkum motorov ch vozidel Institute for Research and Development of Automobiles where he designed an experimental car Rotoped. He lectured at Technical Universities in Prague , Brno and Bratislava . In 1962 in London he received the Herbert Akroyd Stuart Prize given by the Institute of Mechanical Engineers . Mackerle was an author of a number of books and articles. Bibliography Julius Mackerle Americk automobil, Praha 1947 co author V. Gre enko Julius Mackerle Automobilov vzduchem chlazen motory, Praha 1961 Julius Mackerle Air Cooled Motor Engines, Cleaver Hume Press, London 1961 Julius Mackerle Air Cooled Automobile Engines, The Institute of Mechanical Engineers, London 1961 2 Julius Mackerle Automobil dne ka a z t ka, Praha 1977 Julius Mackerle Motory z vodn ch automobil , Praha 1980 Julius Mackerle Automobil s lep i ... more details
The Kuznetsov NK 32 is a military specification afterburning 3 spool low bypass turbofan jet engine which powers the Tupolev Tu 160 supersonic bomber, and was fitted to the later model Tupolev Tu 144 LL supersonic transport . It is the largest and most powerful engine ever fitted on a combat aircraft however, higher thrust engines are fitted to civil aircraft such as General Electric GE90 . Such engines sacrifice exhaust speed for higher thrust and hence cannot accelerate to supersonic speeds . It produces 55,000 lbf 245 kN of thrust in maximum afterburner. Cruise thrust 14 000 kgf 31,000 lbf, 137 kN ref name mil Afterburning thrust 25 000 kgf 55,000 lbf, 245 kN ref name mil http www.jet engine.net miltfspec.html Military Turbojet Turbofan Specifications ref Specific fuel consumption supersonic 1.70 kg kgf hour ref name http www.airforce.ru aircraft tupolev tu 160 book page 1 3.htm 160 Bot generated title ref Specific fuel consumption subsonic 0.72 0.73 kg kgf hour ref name http www.airforce.ru aircraft tupolev tu 160 book page 1 3.htm 160 Bot generated title ref Bypass ratio 1.4 ref name civ http www.jet engine.net civtfspec.html Civil Turbojet Turbofan Specifications Bot generated title ref Overall pressure ratio OPR 28.4 ref name civ Length convert 6000 mm ft abbr on ref name civ Diameter convert 1460 mm ft abbr on ref name civ Dry mass convert 3400 kg lbs abbr on ref name civ References references External links http www.leteckemotory.cz motory nk 32 NK 32 on LeteckeMotory.cz czech Kuznetsov aeroengines Aviation lists engine aircraft stub Category Low bypass turbofan engines Category Kuznetsov aircraft engines Category Turbofan engines 1980 1989 bg 32 es Kuznetsov NK 32 fr Kouznetsov NK 32 it Kuznetsov NK 32 ru 32 ... more details
Infobox Aircraft Begin name DV 2 image Image Lotarev DV 2 Kosice.jpg caption DV 2 turbofan engine Infobox Aircraft Engine type Turbofan national origin Soviet Union Czechoslovakia manufacturer Ivchenko Progress PSLM first run 1987 major applications Aero L 39 Albatros L 39MS Albatros br Aero L 59 Super Albatros L 59 Super Albatros br Hongdu L 15 br Ilyushin Il 108 number built 124 ref name DV 2 http www.janes.com articles Janes Aero Engines PSLM DV 2 Slovakia.html PSLM DV 2 at janes.com ref program cost unit cost developed from Ivchenko Progress AI 25 Ivchenko AI 25 developed into variants with their own articles The Lotarev DV 2 or PSLM DV 2 is a two spool turbofan turbofan engine manufactured in Pova sk Bystrica , Slovakia by Pova sk Stroj rne Leteck Motory PSLM former ZVL and designed in partnership with Ivchenko Progress Ivchenko Lotarev Design Bureau. ref http www.janes.com articles Janes Aero Engines PSLM Povazske Strojarne Letecke Motory a s Slovakia.html PSLM Aero engines manufacturer ref Design and development Developed from the Ivchenko Progress AI 25 Ivchenko AI 25 turbofan engine, ZVL was also responsible for pre production and serial engine production. ref name DV 2 The DV 2 is a two spool modular aviation turbofan engine with a single stage overhung fan, two stage LP compressor, seven stage HP compressor, single stage HP turbine, and two stage LP turbine, and an annular combustion system. Maximum power at T O is 4,850 lbf 21.58 kN with a specific fuel consumption of 0.593lb hr lbf, at Maximum Rating, Sea Level Static, ISA. ref http www.forecastinternational.com archive at ea0448.doc Russia, Central Eastern Europe and China Turbofan and Turbojet Engines ref One of the most unusual features of this military engine is the single stage fan most trainer and combat engines have multi staged fans, single stage fans normally being the preserve of civil and military transport turbofans. Ivchenko Lotarev chose a very low specific thrust net thrust airflow cyc ... more details
This article is a part of Wikipedia WikiProject Aircraft . Please see Wikipedia WikiProject Aircraft page content for recommended layout. Infobox Aircraft Begin name Gnome Rh ne 14M Mars image File Gnome Rhone M05 Mars.JPG caption Un Gnome Rh ne 14M05 Mars Infobox Aircraft Engine type Radial engine national origin manufacturer Gnome et Rh ne first run major applications number built program cost unit cost developed from developed into variants with their own articles The Gnome Rh ne 14M was a small 14 cylinder two row air cooled radial engine that was used on several French and German aircraft of World War II . Applications Breguet 693 Gotha Go 244 Hanriot NC 530 Hanriot NC 600 Henschel Hs 129 Messerschmitt Me 323 Potez 631 Potez 633 Potez 637 Potez 662 Potez 63.11 Specifications 14M 00 01 pistonspecs 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 ref ref name tsygulev cite book last Tsygulev title Aviacionnye motory voennykh vozdushnykh sil inostrannykh gosudarstv lang ru publisher Gosudarstvennoe voennoe izdatelstvo Narkomata Oborony Soyuza SSR location Moscow year 1939 url http base13.glasnet.ru text aviamotory t.htm ref type Fourteen cylinder two row supercharged air cooled radial engine bore 112 mm 4.41 in stroke 116 mm 4.57 in displacement 18.92 l 1,155 in length diameter 950 mm 37.4 in width height weight 410 kg 904 lb valvetrain Two overhead valve s per cylinder supercharger turbocharger fuelsystem Bronzavia carburetor fueltype 87 octane rating gasoline oilsystem coolingsystem Air cooled power br 522 kW 700 hp at 3,030 rpm for takeoff and at 5,150 m 16,900 ft specpower specpower 27.59 kW l 0.61 hp in compres ... more details
The Hispano Suiza 14AB was a 14 cylinder twin row air cooled radial engine. In 1929 the Hispano Suiza company bought a license to produce the Wright Whirlwind engine. The technology from that engine was used to produce a number of different radial engines with greater displacements, power and number of cylinders. The most significant of them was 14AB, which was a very compact design with relatively good performance, and some 2,500 engines were produced. The 14AB suffered from cooling problems, and many aircraft originally designed for the 14AB were redesigned to use the more reliable Gnome Rh ne 14M series of engines or imported Wright and Pratt & Whitney R 1535 engines. Variants 14AB 00 With reduction gear 14AB 02 Without reduction gear 14AB 12 800hp 14AB 13 800hp Applications Potez 630 Breguet 691 Specifications Hispano Suiza 14AB 00 pistonspecs 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 ref ref name tsygulev cite book last Tsygulev title Aviacionnye motory voennykh vozdushnykh sil inostrannykh gosudarstv lang ru publisher Gosudarstvennoe voennoe izdatelstvo Narkomata Oborony Soyuza SSR location Moscow year 1939 url http base13.glasnet.ru text aviamotory t.htm ref type Fourteen cylinder two row supercharged air cooled radial engine bore 135 mm 5.31 in stroke 130 mm 5.12 in displacement 26.05 l 1,590 in length 1,530 mm 60.24 in diameter 1,010 mm 39.76 in width height weight 495 kg 1,091 lb valvetrain Two overhead valve s per cylinder supercharger Single speed centrifugal type supercharger , 9.38 1 reduction turbocharger fuelsystem Carburetor fueltype 87 octane rating gasoline oilsystem coolingsystem Air cooled ... more details
Infobox Aircraft Begin name Sh 22 image caption Infobox Aircraft Engine type Radial engine national origin manufacturer Siemens & Halske Siemens Halske first run major applications number built program cost unit cost developed from developed into variants with their own articles The Siemens Halske Sh 22 also known as SAM 22 was a nine cylinder aircraft radial engine manufactured by Siemens & Halske in Germany in the 1930s. Following the reorganization of its manufacturer and change in military nomenclature, the engine became known as the Bramo 322 . Applications Dornier Do 19 proposed Fieseler Fi 98 Heinkel He 46 Henschel Hs 122 Junkers W 34 Specifications SAM 22B pistonspecs 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 ref ref name tsygulev cite book last Tsygulev title Aviacionnye motory voennykh vozdushnykh sil inostrannykh gosudarstv lang ru publisher Gosudarstvennoe voennoe izdatelstvo Narkomata Oborony Soyuza SSR location Moscow year 1939 url http base13.glasnet.ru text aviamotory t.htm ref type Nine cylinder single row supercharged air cooled radial engine bore 154 mm 6.06 in stroke 160 mm 6.3 in displacement 26.82 l 1,636.8 in length 1,285 mm 50.59 in diameter 1,324 mm 52.13 in width height weight 465 kg 1,025 lb valvetrain Two overhead valve s per cylinder supercharger Single speed centrifugal type supercharger turbocharger fuelsystem Carburetor fueltype 80 octane rating gasoline oilsystem coolingsystem Air cooled power 442 kW 592 hp at 2,100 rpm for takeoff specpower 16.49 kW l 0.36 hp in compression 5.2 1 fuelcon specfuelcon oilcon power weight 0.95 kW kg 0.58 hp lb reduction gear Farman Aviation Works ... more details
The Hispano Suiza 14AA was a fourteen cylinder aircraft radial engine used in France during the late 1930s. As Hispano Suiza lacked recent experience in developing radial engines, it was derived from the licensed Wright R 2600 engine. ref http www.hydroretro.net etudegh hispanosuiza.pdf Hartmann, G rard, Hispano Suiza. Les moteurs de tous les records ref Due to reliability problems, the engine was largely supplanted by the similar Gnome Rh ne 14N . Not to be confused with the smaller Hispano Suiza 14AB , which was derived from the smaller Wright Whirlwind series. Specifications Hispano Suiza 14AA 04 pistonspecs 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 ref ref name tsygulev cite book last Tsygulev title Aviacionnye motory voennykh vozdushnykh sil inostrannykh gosudarstv lang ru publisher Gosudarstvennoe voennoe izdatelstvo Narkomata Oborony Soyuza SSR location Moscow year 1939 url http base13.glasnet.ru text aviamotory t.htm ref type Fourteen cylinder two row supercharged air cooled radial engine bore 156 mm 6.13 in stroke 170 mm 6.69 in displacement 45.25 l 2,761 in length 1,650 mm 64.96 in diameter 1,260 mm 49.61 in width height weight 640 kg 1,411 lb valvetrain Overhead valve s supercharger Single speed centrifugal type supercharger , 10.0 1 reduction turbocharger fuelsystem Carburetor fueltype 85 87 octane rating gasoline oilsystem coolingsystem Air cooled power 793 kW 1,063 hp at 2,125 rpm for takeoff specpower 17.52 kW l 0.39 hp in compression 6.2 1 fuelcon specfuelcon 369 g kW h 0.61 lb hp h oilcon 12 g kW h 0.32 oz hp h power weight 1.24 kW kg 0.75 hp lb reduction gear 1.58 1 Applications Amiot 341 LeO ... more details
This article is about an aircraft engine, for the prototype electric locomotive see AEG 12X Infobox Aircraft Begin name 12X image caption Infobox Aircraft Engine type V 12 engine Vee piston engine national origin France manufacturer Hispano Suiza first run major applications number built program cost unit cost developed from developed into variants with their own articles The Hispano Suiza 12X was an aircraft piston engine designed in France by Hispano Suiza during the early 1930s. A 12 cylinder Vee, liquid cooled design, the 12X was used on several aircraft types, some of them being used in limited numbers during World War II . Due to the 12X s limited power output, its derivative the more powerful Hispano Suiza 12Y had a longer career. Variants Hispano Suiza 12Xbrs Hispano Suiza 12Xcrs Hispano Suiza 12Xgrs Hispano Suiza 12Xhrs Hispano Suiza 12Xirs Hispano Suiza 12Xrs Applications Dewoitine D.500 Bernard 260 Bl riot SPAD S.510 Loire 130 Loire Nieuport LN.40 Lior et Olivier H 246 Morane Saulnier M.S.225 Morane Saulnier M.S. 227 Potez 540 Potez 650 Specifications 12Xcrs pistonspecs 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 ref ref name tsygulev cite book last Tsygulev title Aviacionnye motory voennykh vozdushnykh sil inostrannykh gosudarstv lang ru publisher Gosudarstvennoe voennoe izdatelstvo Narkomata Oborony Soyuza SSR location Moscow year 1939 url http base13.glasnet.ru text aviamotory t.htm ref type Twelve cylinder supercharged liquid cooled 60 V12 engine Vee piston engine bore 130 mm 5.12 in stroke 170 mm 6.69 in displacement 27 L 1,648 in length 1,577 mm 62.09 in diameter width 726 mm 28.58 in height 904 ... more details
This article is a part of Wikipedia WikiProject Aircraft . Please see Wikipedia WikiProject Aircraft page content for recommended layout. Infobox Aircraft Begin name R 1535 Twin Wasp Junior image Image Waspjunior.jpg caption Pratt & Whitney Twin Wasp Junior, at the National Museum of Naval Aviation , Pensacola, Florida Infobox Aircraft Engine type Radial engine manufacturer Pratt & Whitney national origin United States first run 1932 major applications The Pratt & Whitney R 1535 Twin Wasp Junior was an engine used in United States American aircraft in the 1930s. The engine was first introduced in 1932 as a 14 cylinder version of the 9 cylinder R 985. ref Gunston 1989, p.115. ref It was a two row, air cooled radial design. Engine displacement Displacement was 1,535 in 25.2 L bore and stroke were both 5 3 16 in 131.8 mm . Variants R 1535 11 750 hp 559 kW R 1535 13 750 hp 559 kW , 825 hp 615 kW R 1535 44 625 hp 466 kW R 1535 72 650 hp 485 kW R 1535 94 825 hp 615 kW R 1535 96 825 hp 615 kW R 1535 98 700 hp 521 kW R 1535 SB4 G 825 hp 615 kW Applications Bellanca 28 70 Breguet 695 SBC Helldiver Curtiss SBC 3 Helldiver Douglas O 46 Fokker D.XXI Finnish licence built series 4 and 5 Grumman F2F Hughes H 1 Racer Miles Master Northrop A 17 Northrop BT SBU Corsair Vought SBU Corsair SB2U Vindicator Vought SB2U Vindicator Specifications R 1535 SB4 G pistonspecs 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 ref ref name tsygulev cite book last Tsygulev title Aviacionnye motory voennykh vozdushnykh sil inostrannykh gosudarstv lang ru ... more details
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