afterburning turbojet

thrust additional thrust, but it doesn't burn as efficiently as it does in If the aircraft burns a large percentage of its fuel with the afterburner alight, it pays to select an engine cycle with a high specific thrust (i.e. [2], The J85-21 design replaces AM 355 chromium nickel molybdenum stainless steel alloy, used by previous J85 models for compressor rotors and blades, with a titanium alloy. Aircraft Propulsion - Ideal Turbojet Performance. Abdullah Ghori. [18][19], Early British afterburner ("reheat") work included flight tests on a Rolls-Royce W2/B23 in a Gloster Meteor I in late 1944 and ground tests on a Power Jets W2/700 engine in mid-1945. propulsion system. The Pratt & Whitney J75 (civilian designation: JT4A) is an axial-flow turbojet engine first flown in 1955. [29] If the contribution of fuel to the nozzle gross thrust is ignored, the net thrust is: F 5th The best way to choose which conceptual design from several contenders that a company should develop further in preliminary and detail design is: Use a decision matrix Learn how your comment data is processed. Engine: 1 Khatchaturov R-35-300 afterburning turbojet; 28,660 lbs. If you are interested in jet engine design, check out my posts on its history, compressor and turbine design, jet engine optimisation and turbine cooling. Thrust may be increased by burning fuel in a turbofan's cold bypass air, instead of the mixed cold and hot flows as in most afterburning turbofans. These are common in helicopters and hovercraft. These vanes also helped to direct the air onto the blades. ( With more than 75 million flight hours of experience on military and . turbojet,some of the energy of the exhaust from the burner is used to turn the turbine. The total fuel flow tends to increase faster than the net thrust, resulting in a higher specific fuel consumption (SFC). For younger students, a simpler explanation of the information on this page is describing the . Reheat was flight-trialled in 1944 on the W.2/700 engines in a Gloster Meteor I. Please send suggestions/corrections to: benson@grc.nasa.gov. At normal subsonic speeds this reduces the propulsive efficiency, giving an overall loss, as reflected by the higher fuel consumption, or SFC. m document.getElementById( "ak_js_1" ).setAttribute( "value", ( new Date() ).getTime() ); This site uses Akismet to reduce spam. Our thrust equation indicates that net thrust equals {\displaystyle F_{N}\;} If, however, a convergent-divergent de Laval nozzle is fitted, the divergent (increasing flow area) section allows the gases to reach supersonic velocity within the divergent section. gets into cruise. Afterburning is usually used by military fighter aircraft for takeoff and initial climb. [9] The Gloster E.28/39, (also referred to as the "Gloster Whittle", "Gloster Pioneer", or "Gloster G.40") made the first British jet-engined flight in 1941. Contact Glenn. simple way to get the necessary thrust is to add an afterburner to a Two supersonic airliners, Concorde and the Tu-144, also used afterburners as does Scaled Composites White Knight, a carrier aircraft for the experimental SpaceShipOne suborbital spacecraft. must exceed the true airspeed of the aircraft A similar average, single-stage axial compressor increases the pressure by only a factor of 1.2. . of an afterburning turbojet. Modern large turbojet and turbofan engines usually use axial compressors. Further compressed air is introduced which completes the combustion process and reduces the temperature of the combustion products to a level which the turbine can accept. aircraft employ an afterburner on either a low bypass turbofan produced by afterburning. The parts of the engine are described on other slides. Afterburning is an exception to this rule. or turbofan engine, immediately in front of the engine's exhaust nozzle. The resulting combustion process increases the afterburner exit (nozzle entry) temperature significantly, resulting in a steep increase in engine net thrust. The Me 262 in April and the Gloster Meteor in July, so the Meteor only saw around 15 aircraft enter WW2 action , while up to 1400 Me 262 were produced, with 300 entering combat, delivering the first ground attacks and air combat victories of jet planes.[11][12][13]. On early engines, the turbine temperature limit had to be monitored, and avoided, by the pilot, typically during starting and at maximum thrust settings. (You can investigate nozzle operation with our interactive nozzle Europe.) Anurak Atthasit. High bypass-ratio turbofan engines, which are the most common in modern airliners, are designed around this second principle the big fan at the front sucks in tons of air, but because this flow bypasses the combustion chamber, it is not accelerated to a high exit velocity. 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. simple way to get the necessary thrust is to add an afterburner to a For clarity, the engine thrust is then called The Chengdu J-7 (Chinese: -7; third generation export version F-7; NATO reporting name: Fishcan) is a People's Republic of China fighter aircraft.It is a license-built version of the Soviet Mikoyan-Gurevich MiG-21, and thus shares many similarities with the MiG-21. In turbojets the gain is limited to 50%, whereas in a turbofan it depends on the bypass ratio and can be as much as 70%.[17]. r insight into the field." Sims, C.T., Chester, A History of Superalloy Metallurgy, Proc. exit/entry). Most modern passenger and military aircraft are powered by gas turbine engines, which are also called jet engines. Since the jet engine upstream (i.e., before the turbine) will use little of the oxygen it ingests, additional fuel can be burned after the gas flow has left the turbines. [7][8], On 27 August 1939 the Heinkel He 178, powered by von Ohains design, became the world's first aircraft to fly using the thrust from a turbojet engine. The compressed air from the compressor is heated by burning fuel in the combustion chamber and then allowed to . The combustion products leave the combustor and expand through the turbine where power is extracted to drive the compressor. The 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). It features an eight-stage axial-flow compressor powered by two turbine stages, and is capable of generating up to 2,100lbf (9.3kN) of dry thrust, or more with an afterburner. An average, single-stage, centrifugal compressor can increase the pressure by a factor of 4. This process, also known as reheat, is inefficient but can boost turbofan thrust by as much as 50 percent [sources: Encyclopaedia Britannica; Pratt & Whitney ]. "Test Pilot" Brian Trubshaw, Sutton Publishing 1999, "Trade-offs in Jet Inlet Design" Sobester, Journal of Aircraft Vol.44, No.3, MayJune 2007, Fig.12. is given on a separate slide. The hot jet from the turbine flows into the jet pipe at a velocity of around 250 m/s to 400 m/s, and this velocity is far too high to guarantee stable combustion in the jet pipe. The operation of a turbojet is modelled approximately by the Brayton cycle. Where the Chinese interloper scores big is its power plant, using a single WS-10B afterburning turbojet producing in the region of 32,000 lbs of thrust. Additional thrust is generated by the higher resulting exhaust velocity. If the free stream conditions f At full throttle at sea level, this engine, without afterburner, consumes approximately 400 US gallons (1,500L) of fuel per hour. Reheating is defined as "appreciably improving the efficiency of an engine by reheating the working fluid Turbojets are still common in medium range cruise missiles, due to their high exhaust speed, small frontal area, and relative simplicity. With the increased temperature To prevent this a vapour gutter is placed just prior to the fuel injection nozzles that spins the jet into turbulent eddie currents, thereby further slowing down the hot turbine exhaust gases and allowing for a better mixture of fuel and jet stream. Step 2: The power shaft attached to the turbine powers the transmission. A system to trial the technique in the Gloster E.28/39 was devised but never fitted.[27]. The General Electric J85-GE-13 is an afterburning turbojet engine possessing a high thrust-to-weight ratio. . The downside, of course, is increased size and induced drag, which is a nightmare for nimble fighter aircraft. Schematic of afterburning components and functionality at the tail end of a jet engine [1]. Text Only Site In October 1929 he developed his ideas further. basic turbojet of thrust at full power. An ideal afterburning turbojet engine shown below has ideal components with constant gas properties. Older engines had stationary vanes in front of the moving blades. aircraft employ an afterburner on either a low bypass turbofan The compressor is driven by the turbine. {\displaystyle F_{N}={\dot {m}}_{air}(V_{j}-V)}, The speed of the jet [21], General Electric 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.[22]. The ram pressure rise in the intake is the inlet's contribution to the propulsion system's overall pressure ratio and thermal efficiency. The Quail was designed to be released from a B-52 Stratofortress in-flight and fly for long distances in formation with the launch aircraft, multiplying the number of targets facing the SA-2 surface-to-air missile operators on the ground. + 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. In general, a good heuristic to keep in mind when designing anything that moves is that maximising the power output per unit mass leads to a more efficient design. Please send suggestions/corrections to: benson@grc.nasa.gov. Moreover, afterburning turbojet engines allowed to break the sound barrier during a level flight. The first turbojets, used either a centrifugal compressor (as in the Heinkel HeS 3), or an axial compressor (as in the Junkers Jumo 004) which gave a smaller diameter, although longer, engine. In fighter aircraft you want a small and compact engine that provides tons of thrust. National origin: Soviet Union; Status: In limited service; Number built: 1,186; Engine: 2 x Tumansky R-15B-300 afterburning turbojet; Max Speed: Mach 3.2; 3 . of the basic turbojet has been extended and there is now a ring of flame Turbojet - Characteristics and Uses: 1. Liquid injection was tested on the Power Jets W.1 in 1941 initially using ammonia before changing to water and then water-methanol. Air from the compressor is passed through these to keep the metal temperature within limits. These losses are quantified by compressor and turbine efficiencies and ducting pressure losses. the thrust F and the resulting air speed . Otherwise, if pressure is not released, the gas can flow upstream and re-ignite, possibly causing a compressor stall (or fan surge in a turbofan application). [10], The first two operational turbojet aircraft, the Messerschmitt Me 262 and then the Gloster Meteor, entered service in 1944, towards the end of World War II. In the first stage, the turbine is largely an impulse turbine (similar to a pelton wheel) and rotates because of the impact of the hot gas stream. Most modern fighter On this page we will discuss some of the fundamentals Afterburners are used almost exclusively on supersonic aircraft, most being military aircraft. [3], The Iranian Ministry of Defense constructed a new engine based on the General Electric J85-GE-21B named "OWJ" and presented it at a defense exhibition on 22 August 2016. Compressor: single-spool 9 axial stages Combustors: annular Turbine: 2 stages Fuel type: jet fuel. the temperature rise across the unit increases, raising the afterburner fuel flow. Effect of afterburning during take-off and climbing [1], For a fixed airspeed , this means that the level of thrust depends on both the exit jet velocity of the gases and the mass of air flowing through the engine per second. When the afterburner is turned on, fuel is injected and igniters are fired. turned on, additional fuel is injected through the hoops and into the ! It consists of a gas turbine with a propelling nozzle. [20], 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. of the exhaust, the flow area of the nozzle has to be increased to The Welland was type-certified for 80 hours initially, later extended to 150 hours between overhauls, as a result of an extended 500-hour run being achieved in tests. For comparison, modern civil turbofan engines have overall pressure ratios of 44:1 or more. The speed This aircraft application of "reheat" contrasts with the meaning and implementation of "reheat" applicable to gas turbines driving electrical generators and which reduces fuel consumption. {\displaystyle F_{N}=({\dot {m}}_{air}+{\dot {m}}_{f})V_{j}-{\dot {m}}_{air}V}, If the speed of the jet is equal to sonic velocity the nozzle is said to be "choked". in the inlet. 5th Symp. A two-spool design in the 17,000 lbf (76 kN) thrust class, the J75 was essentially the bigger brother of the Pratt & Whitney J57 (JT3C). afterburning turbojet Hot gases leaving the combustor expand through the turbine. This generally means that we can shrink the size of the engine and decrease the bypass ratio to provide better aerodynamic performance. This means that the increased fuel consumption is balanced by the time saved to cover a desired distance or operating manoeuvre. Turbojets. [2] An engine producing maximum thrust wet is at maximum power, while an engine producing maximum thrust dry is at military power. airplane Pre-jet commercial aircraft were designed with as many as four engines in part because of concerns over in-flight failures. Where vehicles are "turbine-powered", this is more commonly by use of a turboshaft engine, a development of the gas turbine engine where an additional turbine is used to drive a rotating output shaft. thrust with afterburner. To get started, check out some of our most interesting posts, listen to the podcast or subscribe to our monthly newsletter. [17], High-temperature alloys were a reverse salient, a key technology that dragged progress on jet engines. and the Concorde supersonic airliner. Turbofans are highly fuel efficient and can deliver high thrust for long periods of time, but the design tradeoff is a large size relative to the power output. byTom In order for fighter planes to fly faster than sound (supersonic), thrust The first designs, e.g. #49 9T Labs is Producing High-Performance Composite Materials Through 3D Printing, Podcast Ep. When the afterburner is This is sometimes used in very high bypass . So to produce highlevels of thrust we can either accelerate the exhaust gases to a greater velocity, or just increase the amount of air that is being sucked into the engine. Turbojets were used on Concorde and the longer-range versions of the TU-144 which were required to spend a long period travelling supersonically. Burning all the oxygen delivered by the compressor stages would create temperatures (3,700F (2,040C)) high enough to significantly weaken the internal structure of the engine, but by mixing the combustion products with unburned air from the compressor at 600F (316C) a substantial amount of oxygen (fuel/air ratio 0.014 compared to a no-oxygen-remaining value 0.0687) is still available for burning large quantities of fuel (25,000lb/h (11,000kg/h)) in an afterburner. 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. Schematic Diagram of Turbofan Engine (Photo credit: Wikipedia). Two forms of general operation was afforded to the powerplant and these needed for take-off actions and supersonic Mach 3.0+ cruise endeavors. The thrust curve and isp curve is *kind of* close to this paper. The basic engine design is quite small, about 17.7 inches (45cm) in diameter, and 45.4 inches (115cm) long. The thrust produced by turbojet engines ranges from 50 lb up to the order of 50,000 lb.The uninstalled thrust-to-engine-weight is constantly increasing and currently is on the order of 4 to 6 lb of thrust for every pound of engine weight.Turbojet engines (actually very low-bypass turbofans) are primarily used in supersonic aircraft and usually have an afterburner that burns added fuel with the . N FLIGHT INVESTIGATION OF AN AIR-COOLED PLUG NOZZLE WITH AN AFTERBURNING TURBOJET by Nick E. Samanich Lewis Research Center SUMMARY. It is also increased by reducing the losses as the flow progresses from the intake to the propelling nozzle. affect thrust and fuel flow. Afterburners are generally used only in military aircraft, and are considered standard equipment on fighter aircraft. The J85 was originally designed to power a large decoy missile, the McDonnell ADM-20 Quail. The burning process in the combustor is significantly different from that in a piston engine. The afterburner is used to put back some The V-383 was powered by a single Pratt & Whitney J57 afterburning turbojet capable of 18,000 lbs. The turbine exit gases still contain considerable energy that is converted in the propelling nozzle to a high speed jet. Although this is an approximation, this equation summarises the essential terms that define aircraft propulsion. A simple way to get the necessary thrust is to add an afterburner to a core turbojet. Turbojets supply bleed air from the compressor to the aircraft for the operation of various sub-systems. ) basic turbojet byTom Small frontal area results in ground clearance problems. A limited amount of data is available concerning the effect of afterburning on engine Experimental results from a previous study at the Lewis Research Center (ref. Use the numbers specified in this engine to calculate (b) the low- and . Some engines used both at the same time. Afterburners offer a mechanically simple way to augment j To a first order, the gross thrust ratio (afterburning/dry) is directly proportional to the root of the stagnation temperature ratio across the afterburner (i.e. this term is largely associated with conditions in the nozzle. 100% (1 rating) Solution: Thermal efficiency of turbo jet engine We will . Gas Turbine Design, Components and System Design Integration, Meinhard T. Schobeiri, The Aircraft Gas Turbine Engine and its operation, Part No. The thrust equation for an afterburning turbojet is then given by the general [15] 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. Compressing the air increases its pressure and temperature. The lower the temperature exiting the turbine and the greater the extent of uncombusted oxygen, the greater the temperature increase in the jet pipe due to afterburning. Guns: 1 23 mm Gryazev-Shipunov GSh-23 L autocannon with 260 rounds. Supersonic flight without afterburners is referred to as supercruise. When the afterburner is New planes were equipped with radars, which gave the opportunity to use the air-to-air missiles as a primary weapon. ) The additional oxygen flow increases the associated temperature rise and available thermodynamic energy in the afterburning system. The J58 engine was developed in the late 1950s by Pratt & Whitney Aircraft Division of United Aircraft Corp. to meet a U.S. Navy requirement. [21], American work on afterburners in 1948 resulted in installations on early straight-wing jets such as the Pirate, Starfire and Scorpion.[22]. + Freedom of Information Act In order for fighter planes to fly faster than sound (supersonic), Fig. This mission demanded a small engine that could nevertheless provide enough power to keep up with the jet bomber. thrust of an afterburning turbojet of a turbojet is given by:[29][30], F As a result of the temperature rise in the afterburner combustor, the gas is accelerated, firstly by the heat addition, known as Rayleigh flow, then by the nozzle to a higher exit velocity than occurs without the afterburner. Parametric Analysis of Afterburning Turbojet Engine for Small-Scale Supersonic UAV. Turbojets. 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. Draw the T-s diagram of the engine b. turned off, the engine performs like a basic turbojet. [14] Modern designs incorporate not only VG nozzles but multiple stages of augmentation via separate spray bars. The afterburner is used to put back some Overseas flight paths were plotted to keep planes within an hour of a landing field, lengthening flights. the basic turbojet has been extended and there is now a ring of flame The final engine type used in the Concorde was the Rolls-Royce/Snecma Olympus 593, an afterburning turbojet designed to be as efficient as possible at high speed. By replacing the propeller used on piston engines with a high speed jet of exhaust, higher aircraft speeds were attainable. Hardpoints: 2 fuselages, 2 wing glove and 2 wing pylons with a capacity of 6,600 lb Intakes have ranged from "zero-length"[25] on the Pratt & Whitney TF33 turbofan installation in the Lockheed C-141 Starlifter, to the twin 65 feet (20m) long, intakes on the North American XB-70 Valkyrie, each feeding three engines with an intake airflow of about 800 pounds per second (360kg/s). A Whittle engine was the first turbojet to run, the Power Jets WU, on 12 April 1937. gets into cruise. At the large end of the range, the GE90-115B fan rotates at about 2,500 RPM, while a small helicopter engine compressor rotates around 50,000 RPM. mathematics How does a turbojet work? However, decreasing the jet exit velocity decreases the thrust unless the mass flow rate is increased as well. The following values and parameters are for an early jet engine, the Pratt & Whitney J57, stationary on the runway,[7] and illustrate the high values of afterburner fuel flow, gas temperature and thrust compared to those for the engine operating within the temperature limitations for its turbine. The aircraft's service ceiling was listed at nearly 50,000 feet and rate-of-climb became 12,150 feet-per-minute.MilitaryFactory.com Other new Navy fighters with afterburners included the Chance Vought F7U-3 Cutlass, powered by two 6,000lbf (27kN) thrust Westinghouse J46 engines. when compared with turbojet, resulting in higher propulsive efficiency (Ref. used to turn the turbine. Solar afterburners used on the F7U Cutlass, F-94 Starfire and F-89 Scorpion, had 2-position eyelid nozzles. The mass flow is also slightly increased by the addition of the afterburner fuel. "As an undergraduate studying aerospace engineering, I have to say this blog is a great resource for gaining extra history and The increase in reliability that came with the turbojet enabled three- and two-engine designs, and more direct long-distance flights. [13], A jet engine afterburner is an extended exhaust section containing extra fuel injectors. m Afterburning is also possible with a turbofan engine. Yes, afterburningprovides more thrust and therefore provides more bang for every gram of jet engine, but it is terribly fuel inefficient. hot exhaust stream of the turbojet. EngineSim Turbojets vs. Turbofans: Performance you'll notice that the nozzle of some of the energy of the exhaust from the burner is i The Foxbat made its first flight in 1964 and a few years later in 1970, it entered the service. Although the low-bypass turbofan (shown in Figure 6) has the same general appearance as a turbofan with a larger bypass ratio, certain . Why the change to axial compressors? m In a piston engine, the burning gases are confined to a small volume, and as the fuel burns, the pressure increases. airliner, Concorde. Since the afterburning exit temperature is effectively fixed,[why?] This system was designed and developed jointly by Bristol-Siddeley and Solar of San Diego. Rolls Royce Technical Publications; 5th ed. The fuel burns and produces To move an The fuel burns and produces 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.[31]. diagram, Lightest specific weight. Afterburning, sometimes also called reheat, is a means of increasing the thrust of a jet engine in order to improve aircraft take-off and climb performance, to accelerate beyond the sound barrier, or in a military setting, for improved combat performance. An afterburner has a limited life to match its intermittent use. Air is drawn into the rotating compressor via the intake and is compressed to a higher pressure before entering the combustion chamber. [16], Turbojet engines had a significant impact on commercial aviation. Afterburning is such an old idea that it is turbosuperchargerimpossible to know who first thought of it. if there is to be a net forward thrust on the airframe. After the turbine, the gases expand through the exhaust nozzle producing a high velocity jet. Therefore, afterburning nozzles must be designed with variable geometry 39 to 1. - Ryan A. Jet engines are used to propel commercial airliners and military aircraft. Set the Engine Early turbojet compressors had low pressure ratios up to about 5:1. An afterburner (or a reheat) is an additional component present on some jet engines, mostly military supersonic aircraft. 4.12 In the afterburning turbojet engine shown, assume constant gas properties and ideal components to calculate (a) ram drag (b) compressor shaft power pc (c) fuel-to-air ratio in the primary burner (d) ty, the limit enthalpy parameter in the gas generator (e) turbine expansion parameter Tt (f) turbine shaft power (g) TAB, the afterburner limit Design, non-linear controller (using MATLAB/SIMULINK) based on predictive control method for an air-breathing launch vehicle. An afterburner (or reheat in British English) is an additional combustion component used on some jet engines, mostly those on military supersonic aircraft. For a 70% increase in thrust the fuel consumption can easily double, but of course this increased fuel consumption is balanced by an improved performance in terms of take-off and climb. The thrust with afterburning is 16,000lbf (71,000N). through the air, [4] Thrust depends on two things: the velocity of the exhaust gas and the mass of the gas exiting the nozzle. gets into cruise. It was liquid-fuelled. Apr. The kinetic energy of the air represents the power input to the system. An afterburner or "reheat jetpipe" is a combustion chamber added to reheat the turbine exhaust gases. When the afterburner is But after a brief test-flight the engine can hardly accelerate to Mach 5. In the Afterburners offer a mechanically simple way to augment 07, 2014. = After the combustion, additional fuel is injected into the combustion chamber in the injection pipe downstream of the turbine to "rewarm" the exhaust gases. I can not recommend this book enough. The nozzle pressure ratio on a turbojet is high enough at higher thrust settings to cause the nozzle to choke. The V Compressor types used in turbojets were typically axial or centrifugal. Benson 25 days ago. Afterburning is achieved by injecting additional fuel into the jet pipe downstream of (i.e. When the afterburner is The injection and combustion of extra fuel in this chamber provide additional thrust for takeoff or supersonic flight. However, the corresponding dry power SFC improves (i.e. high fan pressure ratio/low bypass ratio). Type: afterburning turbojet engine Length: 286 cm Diameter: 53 cm Dry weight: 310 kg. However, because the standard injection rate of kerosene at a good fuel-to-oxygen mixture is only around 1-2 m/s, the kerosene would be rapidly blown away even by the diffused jet stream. Due to their high fuel consumption, afterburners are only used for short duration, high-thrust requirements. 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. turned on, additional fuel is injected through the hoops and into the Afterburners are only used on fighter planes and the supersonic N A spectacular flame combined with high speed makes this a popular display for airshows, or as a finale to fireworks. Lowering fan pressure ratio decreases specific thrust (both dry and wet afterburning), but results in a lower temperature entering the afterburner. burn much more fuel. (The Concorde turns the afterburners off once it

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