1653:
flow progresses from the intake to the propelling nozzle. These losses are quantified by compressor and turbine efficiencies and ducting pressure losses. When used in a turbojet application, where the output from the gas turbine is used in a propelling nozzle, raising the turbine temperature increases the jet velocity. At normal subsonic speeds this reduces the propulsive efficiency, giving an overall loss, as reflected by the higher fuel consumption, or SFC. However, for supersonic aircraft this can be beneficial, and is part of the reason why the
Concorde employed turbojets. Turbojet systems are complex systems therefore to secure optimal function of such system, there is a call for the newer models being developed to advance its control systems to implement the newest knowledge from the areas of automation, so increase its safety and effectiveness.
394:
849:, and fuel tank pressurization. The engine itself needs air at various pressures and flow rates to keep it running. This air comes from the compressor, and without it, the turbines would overheat, the lubricating oil would leak from the bearing cavities, the rotor thrust bearings would skid or be overloaded, and ice would form on the nose cone. The air from the compressor, called secondary air, is used for turbine cooling, bearing cavity sealing, anti-icing, and ensuring that the rotor axial load on its thrust bearing will not wear it out prematurely. Supplying bleed air to the aircraft decreases the efficiency of the engine because it has been compressed, but then does not contribute to producing thrust.
661:
Nevertheless, the 593 met all the requirements of the
Concorde programme. Estimates made in 1964 for the Concorde design at Mach 2.2 showed the penalty in range for the supersonic airliner, in terms of miles per gallon, compared to subsonic airliners at Mach 0.85 (Boeing 707, DC-8) was relatively small. This is because the large increase in drag is largely compensated by an increase in powerplant efficiency (the engine efficiency is increased by the ram pressure rise which adds to the compressor pressure rise, the higher aircraft speed approaches the exhaust jet speed increasing propulsive efficiency).
758:
578:, on 12 April 1937. It was liquid-fuelled. Whittle's team experienced near-panic during the first start attempts when the engine accelerated out of control to a relatively high speed despite the fuel supply being cut off. It was subsequently found that fuel had leaked into the combustion chamber during pre-start motoring checks and accumulated in pools, so the engine would not stop accelerating until all the leaked fuel had burned off. Whittle was unable to interest the government in his invention, and development continued at a slow pace.
668:. Aside from giving faster flight speeds turbojets had greater reliability than piston engines, with some models demonstrating dispatch reliability rating in excess of 99.9%. Pre-jet commercial aircraft were designed with as many as four engines in part because of concerns over in-flight failures. Overseas flight paths were plotted to keep planes within an hour of a landing field, lengthening flights. The increase in reliability that came with the turbojet enabled three- and two-engine designs, and more direct long-distance flights.
767:
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896:) and rotates because of the impact of the hot gas stream. Later stages are convergent ducts that accelerate the gas. Energy is transferred into the shaft through momentum exchange in the opposite way to energy transfer in the compressor. The power developed by the turbine drives the compressor and accessories, like fuel, oil, and hydraulic pumps that are driven by the accessory gearbox.
869:. In a piston engine, the burning gases are confined to a small volume, and as the fuel burns, the pressure increases. In a turbojet, the air and fuel mixture burn in the combustor and pass through to the turbine in a continuous flowing process with no pressure build-up. Instead, a small pressure loss occurs in the combustor.
448:(that drives the compressor). The compressed air from the compressor is heated by burning fuel in the combustion chamber and then allowed to expand through the turbine. The turbine exhaust is then expanded in the propelling nozzle where it is accelerated to high speed to provide thrust. Two engineers,
740:
Allowable turbine entry temperatures have increased steadily over time both with the introduction of superior alloys and coatings, and with the introduction and progressive effectiveness of blade cooling designs. On early engines, the turbine temperature limit had to be monitored, and avoided, by the
1652:
The efficiency of a gas turbine is increased by raising the overall pressure ratio, requiring higher-temperature compressor materials, and raising the turbine entry temperature, requiring better turbine materials and/or improved vane/blade cooling. It is also increased by reducing the losses as the
852:
Compressor types used in turbojets were typically axial or centrifugal. Early turbojet compressors had low pressure ratios up to about 5:1. Aerodynamic improvements including splitting the compressor into two separately rotating parts, incorporating variable blade angles for entry guide vanes and
736:
Water injection was a common method used to increase thrust, usually during takeoff, in early turbojets that were thrust-limited by their allowable turbine entry temperature. The water increased thrust at the temperature limit, but prevented complete combustion, often leaving a very visible smoke
660:
engine. However, joint studies by Rolls-Royce and Snecma for a second generation SST engine using the 593 core were done more than three years before
Concorde entered service. They evaluated bypass engines with bypass ratios between 0.1 and 1.0 to give improved take-off and cruising performance.
872:
The fuel-air mixture can only burn in slow-moving air, so an area of reverse flow is maintained by the fuel nozzles for the approximately stoichiometric burning in the primary zone. Further compressed air is introduced which completes the combustion process and reduces the temperature of the
787:
The intake has to supply air to the engine with an acceptably small variation in pressure (known as distortion) and having lost as little energy as possible on the way (known as pressure recovery). The ram pressure rise in the intake is the inlet's contribution to the propulsion system's
910:
After the turbine, the gases expand through the exhaust nozzle producing a high velocity jet. In a convergent nozzle, the ducting narrows progressively to a throat. The nozzle pressure ratio on a turbojet is high enough at higher thrust settings to cause the nozzle to choke.
783:
into the rotating compressor blades. Older engines had stationary vanes in front of the moving blades. These vanes also helped to direct the air onto the blades. The air flowing into a turbojet engine is always subsonic, regardless of the speed of the aircraft itself.
421:
600:, (also referred to as the "Gloster Whittle", "Gloster Pioneer", or "Gloster G.40") made the first British jet-engined flight in 1941. It was designed to test the Whittle jet engine in flight, and led to the development of the Gloster Meteor.
467:
Turbojets have poor efficiency at low vehicle speeds, which limits their usefulness in vehicles other than aircraft. Turbojet engines have been used in isolated cases to power vehicles other than aircraft, typically for attempts on
2321:
SAMI 2010 • 8th IEEE International
Symposium on Applied Machine Intelligence and Informatics • 28–30 January 2010 • Herl'any, Slovakia (Advanced methods of turbojet engines' control), R. Andoga, L. Főző, L. Madarász and J. Judičák
573:
in a seminal paper in 1926 ("An
Aerodynamic Theory of Turbine Design"). Whittle later concentrated on the simpler centrifugal compressor only, for a variety of practical reasons. A Whittle engine was the first turbojet to run, the
615:, the Me 262 in April and the Gloster Meteor in July. Only about 15 Meteor saw WW2 action but up to 1400 Me 262s were produced, with 300 entering combat, delivering the first ground attacks and air combat victories of jet planes.
964:
An afterburner or "reheat jetpipe" is a combustion chamber added to reheat the turbine exhaust gases. The fuel consumption is very high, typically four times that of the main engine. Afterburners are used almost exclusively on
560:
formally submitted his ideas for a turbojet to his superiors. In
October 1929 he developed his ideas further. On 16 January 1930 in England, Whittle submitted his first patent (granted in 1932). The patent showed a two-stage
1158:
889:. The hottest turbine vanes and blades in an engine have internal cooling passages. Air from the compressor is passed through these to keep the metal temperature within limits. The remaining stages do not need cooling.
761:
Schematic diagram showing the operation of a centrifugal flow turbojet engine. The compressor is driven by the turbine stage and throws the air outwards, requiring it to be redirected parallel to the axis of
873:
combustion products to a level which the turbine can accept. Less than 25% of the air is typically used for combustion, as an overall lean mixture is required to keep within the turbine temperature limits.
918:
is fitted, the divergent (increasing flow area) section allows the gases to reach supersonic velocity within the divergent section. Additional thrust is generated by the higher resulting exhaust velocity.
741:
pilot, typically during starting and at maximum thrust settings. Automatic temperature limiting was introduced to reduce pilot workload and reduce the likelihood of turbine damage due to over-temperature.
2325:
Technical
University of Košice, Department of Cybernetics and Artificial Intelligence, Košice, Slovakia ** Technical University of Košice, Department of Environmental Studies and Information Engineering,
1403:
1472:". If the nozzle is choked, the pressure at the nozzle exit plane is greater than atmospheric pressure, and extra terms must be added to the above equation to account for the pressure thrust.
1552:
733:
in the United States was in a good position to enter the jet engine business due to its experience with the high-temperature materials used in their turbosuperchargers during World War II.
853:
stators, and bleeding air from the compressor enabled later turbojets to have overall pressure ratios of 15:1 or more. After leaving the compressor, the air enters the combustion chamber.
711:
Early German turbojets had severe limitations on the amount of running they could do due to the lack of suitable high temperature materials for the turbines. British engines such as the
1475:
The rate of flow of fuel entering the engine is very small compared with the rate of flow of air. If the contribution of fuel to the nozzle gross thrust is ignored, the net thrust is:
770:
Schematic diagram showing the operation of an axial flow turbojet engine. Here, the compressor is again driven by the turbine, but the air flow remains parallel to the axis of thrust
649:) which gave a smaller diameter, although longer, engine. By replacing the propeller used on piston engines with a high speed jet of exhaust, higher aircraft speeds were attainable.
2418:
803:
propulsion systems where the intake and engine contributions to the total compression were 63%/8% at Mach 2 and 54%/17% at Mach 3+. Intakes have ranged from "zero-length" on the
2379:
585:
patented a similar engine in 1935. His design, an axial-flow engine, as opposed to
Whittle's centrifugal flow engine, was eventually adopted by most manufacturers by the 1950s.
1454:
1207:
1249:
826:
The turbine rotates the compressor at high speed, adding energy to the airflow while squeezing (compressing) it into a smaller space. Compressing the air increases its
1631:
1582:
1283:
1032:
476:
engine, a development of the gas turbine engine where an additional turbine is used to drive a rotating output shaft. These are common in helicopters and hovercraft.
530:. His engine was to be an axial-flow turbojet, but was never constructed, as it would have required considerable advances over the state of the art in compressors.
1603:
1313:
380:
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is extracted to drive the compressor. The turbine exit gases still contain considerable energy that is converted in the propelling nozzle to a high speed jet.
2411:
675:, a key technology that dragged progress on jet engines. Non-UK jet engines built in the 1930s and 1940s had to be overhauled every 10 or 20 hours due to
1995:, Powerplants For The Concord Supersonic Civil Airliner, S.G.Hooker, Proceedings of The Institution of Mechanical Engineers, Summer meeting 1964, p.1227
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1734:
1039:
2128:
1953:
799:
The intake gains prominence at high speeds when it generates more compression than the compressor stage. Well-known examples are the
Concorde and
2404:
1966:
Power for the second-generation SST, Young and
Devriese, Extracts from the 25th Louis Bleriot Lecture, Flight International,11 May 1972, p.659
592:, powered by von Ohain's design, became the world's first aircraft to fly using the thrust from a turbojet engine. It was flown by test pilot
393:
373:
1843:
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for 80 hours initially, later extended to 150 hours between overhauls, as a result of an extended 500-hour run being achieved in tests.
618:
Air is drawn into the rotating compressor via the intake and is compressed to a higher pressure before entering the combustion chamber.
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2160:
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is mixed with the compressed air and burns in the combustor. The combustion products leave the combustor and expand through the
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487:, due to their high exhaust speed, small frontal area, and relative simplicity. They are used on some supersonic
75:
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978:
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444:. The gas turbine has an air inlet which includes inlet guide vanes, a compressor, a combustion chamber, and a
53:
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1930:
842:
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which were required to spend a long period travelling supersonically. Turbojets are common in medium range
82:
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fan rotates at about 2,500 RPM, while a small helicopter engine compressor rotates around 50,000 RPM.
3125:
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64:
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1218:
818:, each feeding three engines with an intake airflow of about 800 pounds per second (360 kg/s).
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Hot gases leaving the combustor expand through the turbine. Typical materials for turbines include
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from the compressor to the aircraft for the operation of various sub-systems. Examples include the
800:
2174:"Trade-offs in Jet Inlet Design" Sobester, Journal of Aircraft Vol.44, No.3, May–June 2007, Fig.12
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Sims, C.T., Chester, A History of Superalloy Metallurgy, Proc. 5th Symp. on Superalloys, 1984.
2042:"sir alec | flame tubes | marshal sir | 1949 | 0598 | Flight Archive"
1993:
https://journals-sagepub-com.wikipedialibrary.idm.oclc.org/doi/pdf/10.1177/0020348363178001159
1911:
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The first patent for using a gas turbine to power an aircraft was filed in 1921 by Frenchman
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before changing to water and then water-methanol. A system to trial the technique in the
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1975:
The Engine For TSR2, J.D.Wragg - TSR2 with Hindsight, Royal Air Force Historical Society,
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An intake, or tube, is needed in front of the compressor to help direct the incoming air
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1976:
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469:
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232:
464:, developed the concept independently into practical engines during the late 1930s.
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1832:
Experimental & Prototype US Air Force Jet Fighters, Jenkins & Landis, 2008
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495:, but most fighters spend little time travelling supersonically, and so employ
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1153:{\displaystyle F_{N}=({\dot {m}}_{air}+{\dot {m}}_{f})V_{j}-{\dot {m}}_{air}V}
830:
and temperature. The smaller the compressor, the faster it turns. The (large)
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technology allowed other countries to produce economically practical engines.
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2372:: 1941 survey with discussion of experimental designs of the 1920s and 1930s.
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In the first stage, the turbine is largely an impulse turbine (similar to a
533:
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2655:
2610:
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is the speed of the jet (the exhaust plume) and is assumed to be less than
969:, most being military aircraft. Two supersonic airliners, Concorde and the
893:
780:
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An animation of an axial compressor. The stationary blades are the stators.
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500:
472:. Where vehicles are "turbine-powered", this is more commonly by use of a
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alloys which allowed extended use without overhaul, engines such as the
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and other types of damage to blades. British engines, however, utilised
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2427:
1913:
The Me 262 Stormbird: From the Pilots Who Flew, Fought, and Survived It
981:
700:
518:, the world's first aircraft to fly purely on turbojet power, using an
473:
204:
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1910:
Heaton, Colin D.; Lewis, Anne-Marien; Tillman, Barrett (15 May 2012).
1821:
Improvements relating to the propulsion of aircraft and other vehicles
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Turbojets were used on Concorde and the longer-range versions of the
352:
239:
199:
1728:
Maxime Guillaume,"Propulseur par réaction sur l'air," French patent
545:, the first British aircraft to fly with a turbojet engine, and the
31:
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2486:
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for 500 hours without maintenance. It was not until the 1950s that
653:
347:
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20:
1863:
The First Jet Pilot – The Story of German Test Pilot Erich Warsitz
1605:
if there is to be a net forward thrust on the airframe. The speed
715:
used better materials giving improved durability. The Welland was
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680:
623:
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970:
569:. Practical axial compressors were made possible by ideas from
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342:
2360:: includes rare videos (Heinkel He 178) and audio commentaries
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2830:
2006:
1645:
The operation of a turbojet is modelled approximately by the
404:
1844:"Frank Whittle, 89, Dies; His Jet Engine Propelled Progress"
619:
16:
Airbreathing jet engine which is typically used in aircraft
2426:
1954:"The Day Germany's First Jet Fighter Soared into History"
503:
to raise exhaust speed for bursts of supersonic travel.
420:
814:, to the twin 65 feet (20 m) long, intakes on the
726:
J85-GE-17A turbojet engine from General Electric (1970)
652:
One of the last applications for a turbojet engine was
2211:"World Encyclopedia of Aero Engines – 5th edition" by
2027:"World Encyclopedia of Aero Engines – 5th edition" by
1823:, British patent no. 347,206 (filed: 16 January 1930).
1398:{\displaystyle ({\dot {m}}_{air}+{\dot {m}}_{f})V_{j}}
436:
which is typically used in aircraft. It consists of a
2110:"Test Pilot" Brian Trubshaw, Sutton Publishing 1999,
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Thrust was most commonly increased in turbojets with
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2304:"Gas Turbine Theory" Cohen, Rogers, Saravanamuttoo,
1752:
Britain's Jet Age: From the Meteor to the Sea Vixen
56:. Unsourced material may be challenged and removed.
2798:Engine-indicating and crew-alerting system (EICAS)
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400:, the first production turbojet in operational use
2831:Full Authority Digital Engine/Electronics (FADEC)
603:The first two operational turbojet aircraft, the
3097:
1253:is the rate of flow of fuel entering the engine
1547:{\displaystyle F_{N}={\dot {m}}_{air}(V_{j}-V)}
2788:Electronic centralised aircraft monitor (ECAM)
1584:must exceed the true airspeed of the aircraft
1211:is the rate of flow of air through the engine
611:, entered service in 1944, towards the end of
2929:
2412:
1633:can be calculated thermodynamically based on
664:Turbojet engines had a significant impact on
374:
2274:
2268:
2232:(2nd ed.). Cambridge University Press.
2227:
1739:(filed: 3 May 1921; issued: 13 January 1922)
2344:Constructing A Turbocharger Turbojet Engine
408:Diagram of a typical gas turbine jet engine
19:For the Hong Kong based ferry company, see
2936:
2922:
2793:Electronic flight instrument system (EFIS)
2419:
2405:
2358:Erich Warsitz, the world's first jet pilot
1622:
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987:Reheat was flight-trialled in 1944 on the
977:, a carrier aircraft for the experimental
865:is significantly different from that in a
381:
367:
1936:
1883:
116:Learn how and when to remove this message
3121:Research and development in Nazi Germany
2223:
2221:
2199:"1947 | 1359 | Flight Archive"
2071:. Flightglobal.com: 448. 25 October 1945
1841:
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1884:Listemann, Phil H. (6 September 2016),
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2378:– Correspondence from the archives of
2159:: CS1 maint: archived copy as title (
2004:
1458:represents the ram drag of the intake
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2917:
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2364:NASA reciprocating Engine Description
2218:
1799:"History – Frank Whittle (1907–1996)"
1748:
1640:
856:
2005:Larson, George C. (April–May 2010),
1842:Foderaro, Lisa W. (10 August 1996).
1464:If the speed of the jet is equal to
914:If, however, a convergent-divergent
54:adding citations to reliable sources
25:
2185:"1960 | Flight | Archive"
1407:represents the nozzle gross thrust
938:Liquid injection was tested on the
633:The first turbojets, used either a
13:
3074:Timeline of heat engine technology
2335:
1887:The Gloster Meteor F.I & F.III
935:. Some engines used both methods.
14:
3137:
2351:
2288:"11.6 Performance of Jet Engines"
2228:Cumpsty, Nicholas (2003). "3.1".
2065:"Rolls-Royce Derwent | 1945"
1777:"Chasing the Sun – Frank Whittle"
1449:{\displaystyle {\dot {m}}_{air}V}
973:, also used afterburners as does
2943:
2661:Thrust specific fuel consumption
2215:, Sutton Publishing, 2006, p.160
2031:, Sutton Publishing, 2006, p.192
1866:, Pen and Sword Books, England,
1202:{\displaystyle {\dot {m}}_{air}}
706:
30:
2382:relating to the development of
2370:Possibilities of Jet Propulsion
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1749:Ellis, Guy (15 February 2016).
1683:Turbojet development at the RAE
671:High-temperature alloys were a
41:needs additional citations for
2710:Propeller speed reduction unit
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1244:{\displaystyle {\dot {m}}_{f}}
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975:Scaled Composites White Knight
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950:was devised but never fitted.
1:
2380:Peterhouse, Cambridge College
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998:
821:
816:North American XB-70 Valkyrie
774:
744:
2256:. NASA Glenn Research Center
1710:. NASA Glenn Research Center
843:environmental control system
7:
2621:Engine pressure ratio (EPR)
2366:: includes a software model
2342:Springer, Edwin H. (2001).
1656:
1034:of a turbojet is given by:
861:The burning process in the
10:
3142:
2888:Auxiliary power unit (APU)
2517:Rotating detonation engine
1890:, Philedition, p. 3,
1468:the nozzle is said to be "
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903:
876:
506:
338:Rotating detonation engine
18:
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2388:Cambridge Digital Library
899:
812:Lockheed C-141 Starlifter
2596:Aircraft engine starting
2386:reciprocating engine in
2376:Whittle Power Jet Papers
2346:. Turbojet Technologies.
2091:"Starting Something Big"
942:in 1941 initially using
929:water/methanol injection
805:Pratt & Whitney TF33
801:Lockheed SR-71 Blackbird
541:/700 engine flew in the
214:External thermal engines
171:Internal thermal engines
2477:Pulse detonation engine
2275:Cumpsty, Jet Propulsion
1626:{\displaystyle V_{j}\;}
1577:{\displaystyle V_{j}\;}
1278:{\displaystyle V_{j}\;}
1027:{\displaystyle F_{N}\;}
565:feeding a single-sided
434:airbreathing jet engine
333:Pulse detonation engine
2666:Thrust to weight ratio
2636:Overall pressure ratio
2631:Jet engine performance
2555:Centrifugal compressor
2472:Gluhareff Pressure Jet
1678:Turbine engine failure
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790:overall pressure ratio
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635:centrifugal compressor
588:On 27 August 1939 the
567:centrifugal compressor
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401:
321:Gluhareff Pressure Jet
3016:Steam (reciprocating)
2903:Ice protection system
2671:Variable cycle engine
2641:Propulsive efficiency
1688:Variable cycle engine
1628:
1600:
1579:
1556:The speed of the jet
1549:
1451:
1400:
1310:
1280:
1246:
1204:
1155:
1029:
769:
760:
752:
725:
536:
514:
423:
415:
407:
396:
2803:Flight data recorder
2565:Constant speed drive
2545:Afterburner (reheat)
1609:
1588:
1560:
1481:
1415:
1329:
1298:
1261:
1219:
1171:
1040:
1010:
810:installation in the
605:Messerschmitt Me 262
554:RAF College Cranwell
299:Air-augmented rocket
50:improve this article
3085:Thermodynamic cycle
2996:Pistonless (Rotary)
2986:Photo-Carnot engine
1860:Warsitz, Lutz 2009
1635:adiabatic expansion
1598:{\displaystyle V\;}
1308:{\displaystyle V\;}
967:supersonic aircraft
923:Thrust augmentation
713:Rolls-Royce Welland
693:de Havilland Goblin
689:Rolls-Royce Derwent
685:Rolls-Royce Welland
666:commercial aviation
137:Aircraft propulsion
131:Part of a series on
3106:English inventions
2705:Propeller governor
2312:, p72-73, fig 3.11
2089:Robert V. Garvin,
1916:. Voyageur Press.
1848:The New York Times
1668:Exoskeletal engine
1641:Cycle improvements
1623:
1595:
1574:
1544:
1446:
1395:
1305:
1275:
1241:
1199:
1150:
1024:
857:Combustion chamber
794:thermal efficiency
772:
764:
755:
728:
691:, and by 1949 the
550:
524:
470:land speed records
426:
418:
410:
402:
316:Valveless pulsejet
3091:
3090:
2911:
2910:
2783:Annunciator panel
2769:
2768:
2684:
2683:
2575:Propelling nozzle
2254:"Turbojet Thrust"
2099:978-1-56347-289-3
1872:978-1-84415-818-8
1708:"Turbojet Engine"
1507:
1462:
1461:
1428:
1373:
1345:
1232:
1184:
1132:
1097:
1069:
906:Propelling nozzle
837:Turbojets supply
552:In 1928, British
442:propelling nozzle
391:
390:
233:Electric aircraft
126:
125:
118:
100:
3133:
3126:1930s in science
2938:
2931:
2924:
2915:
2914:
2898:Hydraulic system
2893:Bleed air system
2883:Air-start system
2746:Counter-rotating
2695:
2694:
2676:Windmill restart
2646:Specific impulse
2616:Compressor stall
2550:Axial compressor
2453:
2452:
2421:
2414:
2407:
2398:
2397:
2347:
2329:
2319:
2313:
2302:
2296:
2295:
2284:
2278:
2272:
2266:
2265:
2263:
2261:
2250:
2244:
2243:
2225:
2216:
2209:
2203:
2202:
2195:
2189:
2188:
2181:
2175:
2172:
2166:
2164:
2158:
2150:
2148:
2146:
2140:
2134:. Archived from
2133:
2125:
2119:
2118:, Appendix VIIIb
2108:
2102:
2087:
2081:
2080:
2078:
2076:
2061:
2055:
2052:
2046:
2045:
2038:
2032:
2025:
2019:
2018:
2002:
1996:
1990:
1984:
1973:
1967:
1964:
1958:
1957:
1950:
1944:
1934:
1928:
1927:
1923:978-1-61058434-0
1907:
1901:
1900:
1881:
1875:
1858:
1852:
1851:
1839:
1833:
1830:
1824:
1817:
1811:
1810:
1808:
1806:
1795:
1789:
1788:
1786:
1784:
1773:
1767:
1766:
1762:978-1-44564901-6
1746:
1740:
1738:
1737:
1733:
1726:
1720:
1719:
1717:
1715:
1704:
1663:Air-start system
1632:
1630:
1629:
1624:
1621:
1620:
1604:
1602:
1601:
1596:
1583:
1581:
1580:
1575:
1572:
1571:
1553:
1551:
1550:
1545:
1534:
1533:
1521:
1520:
1509:
1508:
1500:
1493:
1492:
1455:
1453:
1452:
1447:
1442:
1441:
1430:
1429:
1421:
1404:
1402:
1401:
1396:
1394:
1393:
1381:
1380:
1375:
1374:
1366:
1359:
1358:
1347:
1346:
1338:
1321:of the aircraft
1314:
1312:
1311:
1306:
1284:
1282:
1281:
1276:
1273:
1272:
1250:
1248:
1247:
1242:
1240:
1239:
1234:
1233:
1225:
1208:
1206:
1205:
1200:
1198:
1197:
1186:
1185:
1177:
1165:
1164:
1159:
1157:
1156:
1151:
1146:
1145:
1134:
1133:
1125:
1118:
1117:
1105:
1104:
1099:
1098:
1090:
1083:
1082:
1071:
1070:
1062:
1052:
1051:
1033:
1031:
1030:
1025:
1022:
1021:
993:Gloster Meteor I
731:General Electric
647:Junkers Jumo 004
643:axial compressor
563:axial compressor
528:Maxime Guillaume
398:Junkers Jumo 004
383:
376:
369:
328:Aerospike engine
257:Reaction engines
128:
127:
121:
114:
110:
107:
101:
99:
58:
34:
26:
3141:
3140:
3136:
3135:
3134:
3132:
3131:
3130:
3096:
3095:
3092:
3087:
3078:
3065:
3047:
2947:
2942:
2912:
2907:
2871:
2854:
2845:
2841:Thrust reversal
2818:Engine controls
2812:
2775:
2765:
2741:Contra-rotating
2714:
2680:
2584:
2535:Accessory drive
2527:
2521:
2463:Air turborocket
2445:
2437:
2425:
2354:
2338:
2336:Further reading
2333:
2332:
2320:
2316:
2303:
2299:
2286:
2285:
2281:
2273:
2269:
2259:
2257:
2252:
2251:
2247:
2240:
2226:
2219:
2210:
2206:
2197:
2196:
2192:
2183:
2182:
2178:
2173:
2169:
2152:
2151:
2144:
2142:
2138:
2131:
2129:"Archived copy"
2127:
2126:
2122:
2109:
2105:
2088:
2084:
2074:
2072:
2063:
2062:
2058:
2053:
2049:
2040:
2039:
2035:
2026:
2022:
2011:Air & Space
2003:
1999:
1991:
1987:
1974:
1970:
1965:
1961:
1952:
1951:
1947:
1935:
1931:
1924:
1908:
1904:
1898:
1897:978-291859095-8
1882:
1878:
1859:
1855:
1840:
1836:
1831:
1827:
1819:Frank Whittle,
1818:
1814:
1804:
1802:
1797:
1796:
1792:
1782:
1780:
1775:
1774:
1770:
1763:
1747:
1743:
1735:
1729:
1727:
1723:
1713:
1711:
1706:
1705:
1701:
1696:
1659:
1643:
1616:
1612:
1610:
1607:
1606:
1589:
1586:
1585:
1567:
1563:
1561:
1558:
1557:
1529:
1525:
1510:
1499:
1498:
1497:
1488:
1484:
1482:
1479:
1478:
1431:
1420:
1419:
1418:
1416:
1413:
1412:
1389:
1385:
1376:
1365:
1364:
1363:
1348:
1337:
1336:
1335:
1330:
1327:
1326:
1299:
1296:
1295:
1268:
1264:
1262:
1259:
1258:
1235:
1224:
1223:
1222:
1220:
1217:
1216:
1187:
1176:
1175:
1174:
1172:
1169:
1168:
1135:
1124:
1123:
1122:
1113:
1109:
1100:
1089:
1088:
1087:
1072:
1061:
1060:
1059:
1047:
1043:
1041:
1038:
1037:
1017:
1013:
1011:
1008:
1007:
1001:
962:
956:
948:Gloster E.28/39
925:
916:de Laval nozzle
908:
902:
879:
859:
824:
777:
747:
709:
673:reverse salient
656:which used the
598:Gloster E.28/39
543:Gloster E.28/39
509:
485:cruise missiles
387:
294:Air turborocket
227:Electric motors
147:
122:
111:
105:
102:
59:
57:
47:
35:
24:
17:
12:
11:
5:
3139:
3129:
3128:
3123:
3118:
3113:
3108:
3089:
3088:
3083:
3080:
3079:
3077:
3076:
3070:
3067:
3066:
3064:
3063:
3058:
3052:
3049:
3048:
3046:
3045:
3040:
3038:Thermoacoustic
3035:
3030:
3029:
3028:
3018:
3013:
3008:
3003:
2998:
2993:
2988:
2983:
2978:
2973:
2968:
2963:
2958:
2952:
2949:
2948:
2941:
2940:
2933:
2926:
2918:
2909:
2908:
2906:
2905:
2900:
2895:
2890:
2885:
2879:
2877:
2873:
2872:
2870:
2869:
2864:
2858:
2856:
2847:
2846:
2844:
2843:
2838:
2833:
2828:
2822:
2820:
2814:
2813:
2811:
2810:
2805:
2800:
2795:
2790:
2785:
2779:
2777:
2771:
2770:
2767:
2766:
2764:
2763:
2761:Variable-pitch
2758:
2753:
2748:
2743:
2738:
2736:Constant-speed
2733:
2728:
2722:
2720:
2716:
2715:
2713:
2712:
2707:
2701:
2699:
2692:
2686:
2685:
2682:
2681:
2679:
2678:
2673:
2668:
2663:
2658:
2653:
2648:
2643:
2638:
2633:
2628:
2623:
2618:
2613:
2608:
2603:
2598:
2592:
2590:
2586:
2585:
2583:
2582:
2577:
2572:
2567:
2562:
2557:
2552:
2547:
2542:
2537:
2531:
2529:
2523:
2522:
2520:
2519:
2514:
2509:
2504:
2499:
2494:
2489:
2484:
2479:
2474:
2465:
2459:
2457:
2450:
2448:jet propulsion
2439:
2438:
2424:
2423:
2416:
2409:
2401:
2395:
2394:
2390:
2373:
2367:
2361:
2353:
2352:External links
2350:
2349:
2348:
2337:
2334:
2331:
2330:
2328:
2327:
2314:
2297:
2279:
2267:
2245:
2238:
2230:Jet Propulsion
2217:
2204:
2190:
2176:
2167:
2120:
2103:
2082:
2056:
2047:
2033:
2020:
2007:"Old Faithful"
1997:
1985:
1968:
1959:
1945:
1937:Listemann 2016
1929:
1922:
1902:
1896:
1876:
1853:
1834:
1825:
1812:
1790:
1768:
1761:
1741:
1721:
1698:
1697:
1695:
1692:
1691:
1690:
1685:
1680:
1675:
1670:
1665:
1658:
1655:
1642:
1639:
1619:
1615:
1593:
1570:
1566:
1543:
1540:
1537:
1532:
1528:
1524:
1519:
1516:
1513:
1506:
1503:
1496:
1491:
1487:
1466:sonic velocity
1460:
1459:
1456:
1445:
1440:
1437:
1434:
1427:
1424:
1409:
1408:
1405:
1392:
1388:
1384:
1379:
1372:
1369:
1362:
1357:
1354:
1351:
1344:
1341:
1334:
1323:
1322:
1315:
1303:
1292:
1291:
1289:sonic velocity
1285:
1271:
1267:
1255:
1254:
1251:
1238:
1231:
1228:
1213:
1212:
1209:
1196:
1193:
1190:
1183:
1180:
1149:
1144:
1141:
1138:
1131:
1128:
1121:
1116:
1112:
1108:
1103:
1096:
1093:
1086:
1081:
1078:
1075:
1068:
1065:
1058:
1055:
1050:
1046:
1020:
1016:
1000:
997:
958:Main article:
955:
952:
940:Power Jets W.1
924:
921:
904:Main article:
901:
898:
878:
875:
858:
855:
823:
820:
776:
773:
746:
743:
717:type-certified
708:
705:
609:Gloster Meteor
590:Heinkel He 178
583:Hans von Ohain
547:Gloster Meteor
516:Heinkel He 178
508:
505:
458:Hans von Ohain
454:United Kingdom
424:Hans von Ohain
389:
388:
386:
385:
378:
371:
363:
360:
359:
358:
357:
356:
355:
350:
340:
335:
330:
325:
324:
323:
318:
308:
303:
302:
301:
296:
289:Rocket-powered
286:
285:
284:
279:
274:
260:
259:
253:
252:
251:
250:
249:
248:
237:
236:
235:
224:
223:
222:
211:
210:
209:
208:
207:
202:
191:
186:
185:
184:
165:
164:
140:
139:
133:
132:
124:
123:
38:
36:
29:
15:
9:
6:
4:
3:
2:
3138:
3127:
3124:
3122:
3119:
3117:
3114:
3112:
3109:
3107:
3104:
3103:
3101:
3094:
3086:
3081:
3075:
3072:
3071:
3068:
3062:
3059:
3057:
3054:
3053:
3050:
3044:
3043:Manson engine
3041:
3039:
3036:
3034:
3031:
3027:
3024:
3023:
3022:
3021:Steam turbine
3019:
3017:
3014:
3012:
3009:
3007:
3004:
3002:
2999:
2997:
2994:
2992:
2989:
2987:
2984:
2982:
2979:
2977:
2974:
2972:
2969:
2967:
2964:
2962:
2959:
2957:
2956:Carnot engine
2954:
2953:
2950:
2946:
2939:
2934:
2932:
2927:
2925:
2920:
2919:
2916:
2904:
2901:
2899:
2896:
2894:
2891:
2889:
2886:
2884:
2881:
2880:
2878:
2876:Other systems
2874:
2868:
2865:
2863:
2860:
2859:
2857:
2853:and induction
2852:
2848:
2842:
2839:
2837:
2834:
2832:
2829:
2827:
2824:
2823:
2821:
2819:
2815:
2809:
2808:Glass cockpit
2806:
2804:
2801:
2799:
2796:
2794:
2791:
2789:
2786:
2784:
2781:
2780:
2778:
2772:
2762:
2759:
2757:
2754:
2752:
2749:
2747:
2744:
2742:
2739:
2737:
2734:
2732:
2729:
2727:
2724:
2723:
2721:
2717:
2711:
2708:
2706:
2703:
2702:
2700:
2696:
2693:
2691:
2687:
2677:
2674:
2672:
2669:
2667:
2664:
2662:
2659:
2657:
2654:
2652:
2649:
2647:
2644:
2642:
2639:
2637:
2634:
2632:
2629:
2627:
2624:
2622:
2619:
2617:
2614:
2612:
2609:
2607:
2606:Brayton cycle
2604:
2602:
2599:
2597:
2594:
2593:
2591:
2587:
2581:
2580:Turbine blade
2578:
2576:
2573:
2571:
2568:
2566:
2563:
2561:
2558:
2556:
2553:
2551:
2548:
2546:
2543:
2541:
2538:
2536:
2533:
2532:
2530:
2524:
2518:
2515:
2513:
2510:
2508:
2505:
2503:
2500:
2498:
2495:
2493:
2490:
2488:
2485:
2483:
2480:
2478:
2475:
2473:
2469:
2466:
2464:
2461:
2460:
2458:
2454:
2451:
2449:
2444:
2440:
2436:
2433:
2429:
2422:
2417:
2415:
2410:
2408:
2403:
2402:
2399:
2393:
2391:
2389:
2385:
2381:
2377:
2374:
2371:
2368:
2365:
2362:
2359:
2356:
2355:
2345:
2340:
2339:
2324:
2323:
2318:
2311:
2310:0 582 44927 8
2307:
2301:
2293:
2289:
2283:
2277:, Section 6.3
2276:
2271:
2255:
2249:
2241:
2239:0-521-54144-1
2235:
2231:
2224:
2222:
2214:
2208:
2200:
2194:
2186:
2180:
2171:
2162:
2156:
2141:on 9 May 2016
2137:
2130:
2124:
2117:
2116:0 7509 1838 1
2113:
2107:
2100:
2096:
2092:
2086:
2070:
2066:
2060:
2051:
2043:
2037:
2030:
2024:
2016:
2012:
2008:
2001:
1994:
1989:
1982:
1981:0 9519824 8 6
1978:
1972:
1963:
1955:
1949:
1942:
1938:
1933:
1925:
1919:
1915:
1914:
1906:
1899:
1893:
1889:
1888:
1880:
1873:
1869:
1865:
1864:
1857:
1849:
1845:
1838:
1829:
1822:
1816:
1800:
1794:
1778:
1772:
1764:
1758:
1754:
1753:
1745:
1732:
1725:
1709:
1703:
1699:
1689:
1686:
1684:
1681:
1679:
1676:
1674:
1671:
1669:
1666:
1664:
1661:
1660:
1654:
1650:
1648:
1647:Brayton cycle
1638:
1636:
1617:
1613:
1591:
1568:
1564:
1554:
1538:
1535:
1530:
1526:
1517:
1514:
1511:
1504:
1501:
1494:
1489:
1485:
1476:
1473:
1471:
1467:
1457:
1443:
1438:
1435:
1432:
1425:
1422:
1411:
1410:
1406:
1390:
1386:
1377:
1370:
1367:
1360:
1355:
1352:
1349:
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1319:true airspeed
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991:engines in a
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867:piston engine
864:
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707:Early designs
704:
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678:
677:creep failure
674:
669:
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648:
644:
640:
639:Heinkel HeS 3
636:
631:
629:
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621:
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614:
610:
607:and then the
606:
601:
599:
595:
594:Erich Warsitz
591:
586:
584:
579:
577:
576:Power Jets WU
572:
571:A.A. Griffith
568:
564:
559:
558:Frank Whittle
555:
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450:Frank Whittle
447:
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416:Frank Whittle
414:
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246:Human-powered
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206:
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189:Wankel engine
187:
183:
182:Diesel engine
180:
179:
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177:Piston engine
175:
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144:Shaft engines
142:
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109:
98:
95:
91:
88:
84:
81:
77:
74:
70:
67: –
66:
62:
61:Find sources:
55:
51:
45:
44:
39:This article
37:
33:
28:
27:
22:
3116:Gas turbines
3093:
3056:Beale number
3011:Split-single
2945:Heat engines
2862:Flame holder
2836:Thrust lever
2826:Autothrottle
2656:Thrust lapse
2611:Bypass ratio
2491:
2443:Gas turbines
2435:gas turbines
2343:
2317:
2300:
2291:
2282:
2270:
2258:. Retrieved
2248:
2229:
2213:Bill Gunston
2207:
2193:
2179:
2170:
2143:. Retrieved
2136:the original
2123:
2106:
2090:
2085:
2073:. Retrieved
2068:
2059:
2050:
2036:
2029:Bill Gunston
2023:
2014:
2010:
2000:
1988:
1971:
1962:
1948:
1932:
1912:
1905:
1886:
1879:
1862:
1856:
1847:
1837:
1828:
1815:
1803:. Retrieved
1793:
1781:. Retrieved
1771:
1755:. Amberley.
1751:
1744:
1724:
1712:. Retrieved
1702:
1651:
1644:
1555:
1477:
1474:
1463:
1161:
1036:
1002:
986:
984:spacecraft.
979:SpaceShipOne
963:
937:
933:afterburning
926:
913:
909:
894:pelton wheel
891:
880:
871:
860:
851:
836:
825:
798:
786:
778:
739:
735:
729:
710:
670:
663:
651:
632:
617:
613:World War II
602:
587:
581:In Germany,
580:
551:
525:
501:afterburners
491:such as the
478:
466:
429:
427:
271:
112:
103:
93:
86:
79:
72:
60:
48:Please help
43:verification
40:
3111:Jet engines
3061:West number
2981:Minto wheel
2966:Gas turbine
2776:instruments
2731:Blade pitch
2726:Autofeather
2428:Jet engines
2292:web.mit.edu
2075:14 December
960:Afterburner
954:Afterburner
697:type tested
658:Olympus 593
645:(as in the
637:(as in the
539:Whittle W.2
438:gas turbine
220:Steam power
158:ducted fans
3100:Categories
3001:Rijke tube
2719:Principles
2698:Components
2690:Propellers
2589:Principles
2540:Air intake
2528:components
2526:Mechanical
2502:Turboshaft
1939:, p.
1694:References
999:Net thrust
982:suborbital
847:anti-icing
822:Compressor
775:Air intake
745:Components
701:superalloy
474:turboshaft
205:Turboshaft
150:propellers
106:April 2008
76:newspapers
65:"Turbojet"
3026:Aeolipile
2751:Proprotor
2601:Bleed air
2560:Combustor
2497:Turboprop
2384:Whittle's
2326:Košice,))
1874:, p. 125.
1731:FR 534801
1536:−
1505:˙
1426:˙
1371:˙
1343:˙
1230:˙
1182:˙
1130:˙
1120:−
1095:˙
1067:˙
863:combustor
839:bleed air
832:GE90-115B
641:), or an
497:turbofans
353:Shcramjet
240:Clockwork
200:Turboprop
3033:Stirling
2961:Fluidyne
2867:Jet fuel
2756:Scimitar
2626:Flameout
2570:Impeller
2492:Turbojet
2487:Turbofan
2468:Pulsejet
2432:aircraft
2155:cite web
1805:26 March
1783:26 March
1657:See also
1003:The net
828:pressure
808:turbofan
781:smoothly
695:, being
654:Concorde
499:and use
489:fighters
430:turbojet
348:Scramjet
311:Pulsejet
306:Motorjet
277:Turbofan
272:Turbojet
266:Turbines
242:drives:
194:Turbines
162:propfans
148:driving
21:TurboJET
2971:Hot air
2855:systems
2482:Propfan
2017:(1): 80
1983:, p.120
1673:Jet car
1317:is the
1162:where:
989:W.2/700
944:ammonia
887:Nimonic
883:inconel
877:Turbine
762:thrust.
737:trail.
681:Nimonic
624:turbine
507:History
462:Germany
452:in the
446:turbine
440:with a
282:Propfan
90:scholar
3006:Rocket
2991:Piston
2774:Engine
2651:Thrust
2512:Rocket
2507:Ramjet
2308:
2236:
2165:Fig.26
2145:16 May
2114:
2097:
2069:Flight
1979:
1920:
1894:
1870:
1759:
1736:
1470:choked
1005:thrust
971:Tu-144
900:Nozzle
626:where
596:. The
556:cadet
522:engine
493:MiG-25
481:Tu-144
432:is an
343:Ramjet
154:rotors
92:
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63:
2456:Types
2260:6 May
2139:(PDF)
2132:(PDF)
2101:, p.5
1801:. BBC
1779:. PBS
1714:6 May
628:power
520:HeS 3
97:JSTOR
83:books
2851:Fuel
2446:and
2430:and
2306:ISBN
2262:2009
2234:ISBN
2161:link
2147:2016
2112:ISBN
2095:ISBN
2077:2013
1977:ISBN
1918:ISBN
1892:ISBN
1868:ISBN
1807:2010
1785:2010
1757:ISBN
1716:2009
885:and
792:and
687:and
620:Fuel
537:The
456:and
428:The
69:news
2976:Jet
931:or
460:in
160:or
152:,
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