How an airplane jet engine works. How does a jet engine work? How much work did the jet engine do?

For the first time an aircraft with a turbojet engine ( TRD) took to the air in 1939. Since then, the design of aircraft engines has improved, there have been different kinds, but the principle of operation for all of them is approximately the same. To understand why an aircraft with such a large mass can take to the air so easily, you need to understand how an aircraft engine works. A turbojet engine propels an aircraft using jet propulsion. In turn, jet thrust is the recoil force of the gas jet that flies out of the nozzle. That is, it turns out that the turbojet installation pushes the plane and all the people in the cabin with the help of a gas jet. The jet stream, flying out of the nozzle, is repelled from the air and thus sets the aircraft in motion.

Turbofan engine device

Design

The device of the aircraft engine is quite complicated. Working temperature in such installations reaches 1000 and more degrees. Accordingly, all the parts that make up the engine are made of materials that are resistant to high temperatures and fire. Due to the complexity of the device, there is a whole field of science about turbojet engines.

TRD consists of several main elements:

• fan;
• compressor;
• the combustion chamber;
• turbine;
• nozzle.

A fan is installed in front of the turbine. With its help, air is drawn into the unit from the outside. In such installations, fans with a large number of blades of a certain shape are used. The size and shape of the blades provide the most efficient and fast air supply to the turbine. They are made from titanium. In addition to the main function (drawing in air), the fan solves another important task: it is used to pump air between the elements of the turbojet engine and its shell. Due to this pumping, the system is cooled and the destruction of the combustion chamber is prevented.

The compressor is located next to the fan high power. With its help, air enters the combustion chamber under high pressure. In the chamber, air is mixed with fuel. The resulting mixture is ignited. After ignition, the mixture and all adjacent elements of the installation are heated. The combustion chamber is most often made of ceramic. This is due to the fact that the temperature inside the chamber reaches 2000 degrees or more. And ceramics is characterized by resistance to high temperatures. After ignition, the mixture enters the turbine.

View of the aircraft engine from the outside

The turbine is a device consisting of a large number shoulder blades. The flow of the mixture exerts pressure on the blades, thereby setting the turbine in motion. The turbine, due to this rotation, causes the shaft on which the fan is mounted to rotate. It turns out a closed system, which for the operation of the engine requires only the supply of air and the presence of fuel.

Next, the mixture enters the nozzle. This is the final stage of the 1st engine cycle. This is where the jet stream is formed. This is how an airplane engine works. Fan blows cold air into the nozzle, preventing its destruction from excessively hot mixture. The cold air flow prevents the nozzle collar from melting.

Various nozzles can be installed in aircraft engines. The most perfect are considered mobile. The movable nozzle is able to expand and contract, as well as adjust the angle by setting right direction jet stream. Aircraft with such engines are characterized by excellent maneuverability.

Types of engines

Aircraft engines are of various types:

• classic;
• turboprop;
• turbofan;
• straight-through.

Classic installations work according to the principle described above. Such engines are installed on aircraft various modifications. Turboprop function somewhat differently. In them, the gas turbine has no mechanical connection with the transmission. These installations drive the aircraft with the help of jet thrust only partially. The bulk of the hot mix energy this species installation uses to drive the propeller through the gearbox. In such an installation, instead of one, there are 2 turbines. One of them drives the compressor, and the second - the screw. Unlike classic turbojet, screw installations are more economical. But they do not allow aircraft to develop high speeds. They are installed on low-speed aircraft. TRD allow to develop much great speed During the flight.

Turbofans engines are combined units that combine elements of turbojet and turboprop engines. They are different from classic big size fan blades. Both the fan and propeller operate at subsonic speeds. The speed of air movement is reduced due to the presence of a special fairing in which the fan is placed. Such engines consume fuel more economically than classic ones. In addition, they are more high efficiency. Most often they are installed on liners and large-capacity aircraft.

Aircraft engine size relative to human height

Direct-flow air-jet installations do not involve the use of moving elements. Air is drawn in naturally thanks to a fairing mounted on the inlet. After the intake of air, the engine works similarly to the classic one.

Some aircraft fly on turboprop engines, which are much simpler than turbojet engines. Therefore, many people have a question: why use more complex installations, if you can limit yourself to a screw one? The answer is simple: turbojet engines are superior in power to screw engines. They are ten times more powerful. Accordingly, the turbojet engine produces much more thrust. This makes it possible to lift large aircraft into the air and fly at high speed.

In contact with

Jet engine

Jet engine

an engine whose thrust is created by the reaction (recoil) of the jet of the working fluid flowing from it. The working fluid in relation to engines is understood as a substance (gas, liquid, solid body), with the help of which the heat released during the combustion of fuel is converted into useful mechanical work. The basis of a jet engine is where it is burned (source of primary energy) and generated - hot gases (fuel combustion products).

According to the method of generating the working body jet engines subdivided into air-jet (WRD) and rocket engines (RD). In jet engines, fuel is burned in air flow(oxidized by atmospheric oxygen), turning into the thermal energy of hot gases, which in turn is converted into the kinetic energy of the jet stream. Depending on the method of supplying air to the combustion chamber, turbocompressor, ramjet and pulse jet engines are distinguished.

In a turbocharged engine, air is forced into the combustion chamber by a compressor. These motors are the main type aircraft engine. They are divided into turboprop, turbojet and pulse jet engines.

Turboprop engine (TVD) - turbocompressor, in which thrust is mainly created by a propeller driven into rotation gas turbine, and partly by direct reaction of the flow of gases flowing from the jet nozzle.

1 - air; 2 - compressor; 3 - gas; 4 - nozzle; 5 - hot gases; 6 - combustion chamber; 7 - liquid fuel; 8 - nozzles

A turbojet engine (TRD) is a turbocharged engine in which thrust is created by the direct reaction of a stream of compressed gases flowing from a nozzle. Throbbing jet engine- a jet engine in which air periodically entering the combustion chamber is compressed under the action of a velocity pressure. Has little traction used mainly on subsonic aircraft. A ramjet engine (ramjet) is a jet engine in which the air continuously entering the combustion chamber is compressed under the action of a velocity pressure. It has great thrust at supersonic flight speeds; there is no static thrust, so a forced start is necessary for the ramjet.

Encyclopedia "Technology". - M.: Rosman. 2006 .

Jet engine

direct reaction engine, - code name big class engines for aircraft for various purposes. Unlike power plant With piston engine internal combustion and a propeller, where the traction force is created as a result of the interaction of the propeller with external environment, R. D. creates a driving force, called reactive force or thrust, as a result of the outflow from it of a jet of a working fluid that has kinetic energy. This force is directed opposite to the outflow of the working fluid. In this case, the propeller itself is the prime mover. The primary energy necessary for the operation of the propellant, as a rule, is contained in the working fluid itself (the chemical energy of the combusted fuel, the potential energy of the compressed gas).
R. d. are divided into two main groups. The first group consists of rocket engines - engines that create traction only due to the working fluid stored on board aircraft. These include liquid rocket engines, solid fuel rocket engines, electric rocket engines, etc. They are used in rockets for various purposes, including powerful boosters that serve to output spaceships into orbit.
The second group includes jet engines, in which the main component of the working fluid is air taken into the engine from environment. In rocket engines - turbojet engines, ramjet engines, pulse jet engines - all propulsion is generated by direct reaction. by workflow and design features some aircraft are adjacent to air-rocket engines gas turbine engines indirect reaction - turboprop engines and their varieties (turbopropfan engines and turboshaft engines), in which the proportion tractive effort due to the direct reaction is negligible or it is practically absent. Turbojet dual circuit engines with different values ​​of the bypass ratio occupy in this sense an intermediate position between turbojet engines and turboprop engines. Air-rocket engines are used mainly in aviation as part of the power plant of military and civil purpose. Using ambient air as an oxidizing agent, air-rocket engines provide significantly greater fuel efficiency than rocket engines, since only fuel is needed on board the aircraft. At the same time, the possibility of carrying out a working process using ambient air limits the scope of use of air-rocket engines to the atmosphere.
The main advantage of a rocket engine over an air-rocket engine is its ability to operate at any speed and flight altitude (the thrust of a rocket engine does not depend on flight speed and increases with altitude). In some cases, combined engines are used that combine the features of rocket and air-rocket engines. IN combined engines to improve efficiency, air is used at the initial stage of acceleration with the transition to rocket mode at high flight altitudes.

Aviation: Encyclopedia. - M.: Great Russian Encyclopedia. Chief Editor G.P. Svishchev. 1994 .

See what a "jet engine" is in other dictionaries:

JET ENGINE, an engine that provides propulsion by quickly releasing a jet of liquid or gas in a direction opposite to the direction of movement. To create a high-speed flow of gases, fuel in a jet engine ... ... Scientific and technical encyclopedic dictionary

An engine that creates the traction force necessary for movement by converting the initial energy into the kinetic energy of the jet stream of the working fluid; as a result of the expiration of the working fluid from the engine nozzle, ... ... Big soviet encyclopedia

- (direct reaction engine) an engine whose thrust is created by the reaction (recoil) of the working fluid flowing from it. Subdivided into air jet and rocket engines ... Big Encyclopedic Dictionary

An engine that converts any type of primary energy into the kinetic energy of the working fluid (jet stream), which creates jet thrust. In a jet engine, the engine itself and the propulsion unit are combined. The main part of any ... ... Marine dictionary

JET engine, an engine whose thrust is created by direct reaction (recoil) of the working fluid flowing out of it (for example, combustion products of chemical fuel). They are divided into rocket engines (if stocks of the working fluid are placed ... ... Modern Encyclopedia

Jet engine- JET ENGINE, an engine whose thrust is created by direct reaction (recoil) of the working fluid flowing out of it (for example, combustion products of chemical fuel). They are divided into rocket engines (if stocks of the working fluid are placed ... ... Illustrated Encyclopedic Dictionary

JET ENGINE- a direct reaction engine, the reactive (see) of which is created by the return of the jet of the working fluid flowing from it. There are air-jet and rocket (see) ... Great Polytechnic Encyclopedia

jet engine- — Topics oil and gas industry EN jet engine … Technical Translator's Handbook

Space Shuttle rocket engine tests ... Wikipedia

- (direct reaction engine), an engine whose thrust is created by the reaction (recoil) of the working fluid flowing from it. They are divided into air jet and rocket engines. * * * JET ENGINE JET ENGINE (direct motor… … encyclopedic Dictionary

Books

• Aircraft model pulsating air-jet engine , V. A. Borodin , The book covers the design, operation and elementary theory of a pulsating WFD. The book is illustrated with diagrams of jet aircraft models. Reproduced in the original… Category: Agricultural machines Publisher: YoYo Media, Manufacturer:

The rotating propeller pulls the aircraft forward. But the jet engine high speed ejects hot exhaust gases to the rear and thereby creates a reactive thrust force directed forward.

Types of jet engines

There are four types of jet or gas turbine engines:

Turbojet;

Turbofans- such as those used on Boeing-747 passenger liners;

Turboprop where they use propellers driven by turbines;

And Turboshaft that put on helicopters.

turbofan engine consists of three main parts: a compressor, a combustion chamber and a turbine that provides energy. First, air enters the engine and is compressed by a fan. Then, in the combustion chamber, compressed air mixes with fuel and burns, forming gas at high temperature And high pressure. This gas passes through the turbine, causing it to rotate at a tremendous speed, and is thrown back, thus creating a forward thrust force.

Image is clickable

Once in turbine engine The air goes through several stages of compression. The pressure and volume of the gas increase especially strongly after passing through the combustion chamber. The thrust generated by the exhaust gases allows jet aircraft to travel at altitudes and speeds far in excess of those available to piston-engined rotorcraft.

In a turbojet engine, air is taken in from the front, compressed, and combusted along with the fuel. resulting from combustion traffic fumes generate reactive thrust.

Turboprops connect jet thrust exhaust gases with forward thrust generated by the rotation of the propeller.

A jet engine is a device that creates the traction force required for movement by converting the internal energy of the fuel into the kinetic energy of the jet stream of the working fluid.

Jet engine classes:

All jet engines are divided into 2 classes:

• Air-jet - heat engines, using the energy of the oxidation of air obtained from the atmosphere. In these engines working body represented by a mixture of combustion products with other elements of the selected air.
• Rocket - engines that contain everything on board necessary components and are able to work even in vacuum.

The ramjet engine is the simplest in the class of VJE in terms of design. The pressure increase required for the operation of the device is formed by braking the oncoming air flow.

The ramjet workflow can be briefly described as follows:

• Air enters the engine inlet at flight speed, its kinetic energy is converted into internal energy, the air pressure and temperature increase. At the inlet to the combustion chamber and along the entire length of the flow path, the maximum pressure is observed.

• Heating compressed air in the combustion chamber occurs by oxidizing the supplied air, while the internal energy of the working fluid increases.
• Further, the flow narrows in the nozzle, the working fluid reaches sonic speed, and again, when expanding, it reaches supersonic speed. Due to the fact that the working fluid moves at a speed exceeding the speed of the oncoming flow, a jet thrust is created inside.

IN constructively ramjet is limiting simple device. The engine has a combustion chamber, inside which fuel comes from fuel injectors and air from the diffuser. The combustion chamber ends with an entrance to the nozzle, which is narrowing-expanding.

The development of mixed solid fuel technology has led to the use of this fuel in ramjet engines. In the combustion chamber there is a fuel block with a central longitudinal channel. Passing through the channel, the working fluid gradually oxidizes the surface of the fuel and heats up itself. The use of solid fuel further simplifies the engine design: fuel system becomes unnecessary.

Mixed fuel in its composition in a ramjet engine differs from that used in a solid propellant rocket engine. If in rocket engine Since most of the fuel composition is occupied by an oxidizer, in ramjet it is used in small proportions to activate the combustion process.

The ramjet mixed fuel filler mainly consists of a fine powder of beryllium, magnesium or aluminum. Their heat of oxidation significantly exceeds the heat of combustion of hydrocarbon fuel. As an example of a solid-propellant ramjet, one can cite the propulsion engine of the P-270 Moskit cruise anti-ship missile.

The ramjet thrust depends on the flight speed and is determined based on the influence of several factors:

• The higher the flight speed, the greater will be the air flow passing through the engine path, respectively, large quantity oxygen will penetrate into the combustion chamber, which increases fuel consumption, heat and mechanical power motor.
• The greater the air flow through the engine path, the higher the thrust generated by the motor. However, there is a certain limit, the air flow through the motor path cannot increase indefinitely.
• As the flight speed increases, the pressure level in the combustion chamber increases. As a result, the thermal efficiency of the engine is increased.
• How more difference between the speed of the flight of the apparatus and the speed of passage of the jet stream, the greater the thrust of the engine.

The dependence of the thrust of a ramjet engine on the flight speed can be represented as follows: until the flight speed is much lower than the speed of the passage of the jet, the thrust will increase along with the growth of the flight speed. When the flight speed approaches the speed of the jet stream, the thrust begins to fall, having passed a certain maximum, at which optimal speed flight.

Depending on the flight speed, the following categories of ramjet engines are distinguished:

• subsonic;
• supersonic;
• hypersonic.

Each group has its own distinctive features designs.

Subsonic ramjet

This group of engines is designed to provide flights at speeds from 0.5 to 1.0 Mach. Air compression and braking in such engines occurs in a diffuser - an expanding channel of the device at the flow inlet.

These engines are extremely low efficiency. When flying at a speed of M = 0.5, the level of pressure increase in them is 1.186, which is why the ideal thermal efficiency for them is only 4.76%, and if we also take into account losses in real engine, this value will approach zero. This means that when flying at speeds M<0,5 дозвуковой ПВРД неработоспособен.

But even at the limiting speed for the subsonic range at M=1, the level of pressure increase is 1.89, and the ideal thermal coefficient is only 16.7%. These indicators are 1.5 times less than those of reciprocating internal combustion engines, and 2 times less than those of gas turbine engines. Gas turbine and reciprocating engines are also efficient for use when operating in a stationary position. Therefore, ramjet subsonic engines, in comparison with other aircraft engines, turned out to be uncompetitive and are not currently mass-produced.

Supersonic ramjets

Supersonic ramjet engines are designed for flights in the speed range 1< M < 5.

The deceleration of a supersonic gas flow is always performed discontinuously, and a shock wave is formed, which is called a shock wave. At the distance of the shock wave, the process of gas compression is not isentropic. Consequently, losses of mechanical energy are observed, the level of pressure increase in it is smaller than in an isentropic process. The more powerful the shock wave, the more the flow velocity at the front will change, respectively, the greater the pressure loss, sometimes reaching 50%.

In order to minimize pressure losses, compression is organized not in one, but in several shock waves with a lower intensity. After each of these jumps, there is a decrease in the flow velocity, which remains supersonic. This is achieved if the shock front is at an angle to the direction of the flow velocity. The flow parameters in the intervals between jumps remain constant.

In the last jump, the speed reaches a subsonic indicator, further deceleration and air compression processes occur continuously in the diffuser channel.

If the motor inlet is located in the area of ​​undisturbed flow (for example, in front of the aircraft at the nose end or at a sufficient distance from the fuselage on the wing console), it is asymmetric and is completed with a central body - a sharp long "cone" emerging from the shell. The central body is designed to create oblique shock waves in the oncoming air flow, which provide compression and deceleration of air until it enters a special channel of the inlet device. The presented inlet devices are called conical flow devices, the air inside them circulates, forming a conical shape.

The central conical body can be equipped with a mechanical drive, which allows it to move along the axis of the engine and optimize the deceleration of the air flow at different flight speeds. These input devices are called adjustable.

When fixing the engine under the wing or from the bottom of the fuselage, that is, in the area of ​​aerodynamic influence of aircraft structural elements, two-dimensional flow inlet devices are used. They are not equipped with a central body and have a rectangular cross section. They are also called mixed or internal compression devices, since external compression here takes place only with shock waves formed at the leading edge of the wing or nose end of the aircraft. Rectangular inlet adjustable devices are able to change the position of the wedges inside the channel.

In the supersonic speed range, the ramjet is more efficient than in the subsonic range. For example, at a flight speed of M=3, the degree of pressure increase is 36.7, which is close to that of turbojet engines, and the calculated ideal efficiency reaches 64.3%. In practice, these indicators are lower, but at speeds in the range of M = 3-5, the SPVJE is superior in efficiency to all existing types of SPVJ.

At an undisturbed air flow temperature of 273°K and an aircraft speed of M=5, the temperature of the working retarded body is 1638°K, at a speed of M=6 - 2238°K, and in real flight, taking into account shock waves and the action of the friction force, it becomes even higher.

Further heating of the working fluid is problematic due to the thermal instability of the structural materials that make up the engine. Therefore, the speed limit for the SPVRD is M=5.

Hypersonic ramjet engine

The category of hypersonic ramjet includes ramjet, which operates at speeds of more than 5M. As of the beginning of the 21st century, the existence of such an engine was only hypothetical: not a single sample was assembled that would pass flight tests and confirm the feasibility and relevance of its serial production.

At the entrance to the scramjet device, air deceleration is performed only partially, and during the rest of the stroke, the movement of the working fluid is supersonic. At the same time, most of the initial kinetic energy of the flow is retained; after compression, the temperature is relatively low, which makes it possible to release a significant amount of heat to the working fluid. After the input device, the flow part of the engine expands along its entire length. Due to the combustion of fuel in a supersonic flow, the working fluid is heated, it expands and accelerates.

This type of engine is designed for flights in the rarefied stratosphere. Theoretically, such an engine can be used on reusable spacecraft carriers.

One of the main problems in the design of scramjet engines is the organization of fuel combustion in a supersonic flow.

In different countries, several programs have been launched to create a scramjet, all of them are at the stage of theoretical research and pre-design laboratory studies.

Where are ramjets used

The ramjet does not operate at zero speed and low airspeeds. An aircraft with such an engine requires the installation of auxiliary drives on it, which can be a solid-fuel rocket booster or a carrier aircraft from which the aircraft with a ramjet is launched.

Due to the inefficiency of the ramjet at low speeds, it is practically inappropriate to use it on manned aircraft. Such engines are preferably used for unmanned, cruise, disposable combat missiles due to their reliability, simplicity and low cost. Ramjet engines are also used in flying targets. The competition in terms of the characteristics of the ramjet is only a rocket engine.

Nuclear ramjet

During the Cold War between the USSR and the USA, projects of ramjet engines with a nuclear reactor were created.

In such units, the energy source was not the chemical reaction of fuel combustion, but the heat generated by a nuclear reactor installed instead of a combustion chamber. In such a ramjet, air entering through the inlet device penetrates into the active region of the reactor, cools the structure and heats up to 3000 K itself. Then it flows out of the engine nozzle at a speed close to the speed of perfect rocket engines. Nuclear ramjet engines were intended for installation in intercontinental cruise missiles carrying a nuclear charge. Designers in both countries have created small-sized nuclear reactors that fit into the dimensions of a cruise missile.

In 1964, as part of the Tory and Pluto nuclear ramjet research programs, stationary firing tests of the Tory-IIC nuclear ramjet were conducted. The test program was closed in July 1964, and the engine was not flight tested. The alleged reason for curtailing the program could be the improvement in the configuration of ballistic missiles with rocket chemical engines, which made it possible to carry out combat missions without the involvement of nuclear ramjet engines.

Jet motion is a process in which one of its parts is separated from a certain body at a certain speed. The force that arises in this case works by itself, without the slightest contact with external bodies. Jet propulsion was the impetus for the creation of a jet engine. The principle of its operation is based precisely on this force. How does such an engine work? Let's try to figure it out.

Historical facts

The idea of ​​using jet thrust, which would make it possible to overcome the force of gravity of the Earth, was put forward in 1903 by the phenomenon of Russian science - Tsiolkovsky. He published a whole study on the subject, but it was not taken seriously. Konstantin Eduardovich, having survived the change in the political system, spent years of work to prove to everyone that he was right.

Today there are a lot of rumors that the revolutionary Kibalchich was the first in this matter. But the will of this man by the time of the publication of the works of Tsiolkovsky was buried along with Kibalchich. In addition, it was not a full-fledged work, but only sketches and sketches - the revolutionary could not bring a reliable basis for theoretical calculations in his works.

How does reactive force work?

To understand how a jet engine works, you need to understand how this force works.

So, imagine a shot from any firearm. This is a clear example of the action of a reactive force. A jet of hot gas, which was formed during the combustion of the charge in the cartridge, pushes the weapon back. The more powerful the charge, the stronger the return will be.

And now imagine the process of ignition of a combustible mixture: it takes place gradually and continuously. This is exactly what the principle of operation of a ramjet engine looks like. A rocket with a solid propellant jet engine works in a similar way - this is the simplest of its variations. Even novice rocket modellers are familiar with it.

As a fuel for jet engines, black powder was first used. Jet engines, the principle of which was already more advanced, required fuel with a base of nitrocellulose, which was dissolved in nitroglycerin. In large units that launch rockets that put shuttles into orbit, today they use a special mixture of polymer fuel with ammonium perchlorate as an oxidizing agent.

The principle of operation of the RD

Now it is worth understanding the principle of operation of a jet engine. To do this, you can consider the classics - liquid engines, which have not changed much since the time of Tsiolkovsky. These units use fuel and an oxidizer.

As the latter, liquid oxygen or nitric acid is used. Kerosene is used as fuel. Modern cryogenic-type liquid engines consume liquid hydrogen. When oxidized with oxygen, it increases the specific impulse (by as much as 30 percent). The idea that hydrogen could be used was also born in Tsiolkovsky's head. However, at that time, due to the extreme explosiveness, it was necessary to look for another fuel.

The principle of operation is as follows. The components enter the combustion chamber from two separate tanks. After mixing, they turn into a mass, which, when burned, releases a huge amount of heat and tens of thousands of atmospheres of pressure. The oxidant is fed into the combustion chamber. The fuel mixture, as it passes between the double walls of the chamber and the nozzle, cools these elements. Further, the fuel, heated by the walls, will enter the ignition zone through a huge number of nozzles. The jet, which is formed with a nozzle, breaks out. Due to this, a pushing moment is provided.

Briefly, the principle of operation of a jet engine can be compared with a blowtorch. However, the latter is much simpler. There are no various auxiliary engine systems in the scheme of its operation. And these are compressors needed to create injection pressure, turbines, valves, as well as other elements, without which a jet engine is simply impossible.

Despite the fact that liquid engines consume a lot of fuel (fuel consumption is approximately 1000 grams per 200 kilograms of cargo), they are still used as marching units for launch vehicles and shunting units for orbital stations, as well as other spacecraft.

Device

A typical jet engine is arranged as follows. Its main nodes are:

Compressor;

combustion chamber;

Turbines;

Exhaust system.

Let's consider these elements in more detail. The compressor consists of several turbines. Their job is to suck in and compress air as it passes through the blades. The compression process increases the temperature and pressure of the air. Part of this compressed air is fed into the combustion chamber. In it, air is mixed with fuel and ignition occurs. This process further increases the thermal energy.

The mixture exits the combustion chamber at high speed and then expands. Then it follows another turbine, the blades of which rotate due to the action of gases. This turbine, connected to the compressor located in front of the unit, sets it in motion. Air heated to high temperatures exits through the exhaust system. The temperature, already high enough, continues to rise due to the throttling effect. Then the air comes out completely.

aircraft motor

Aircraft also use these engines. So, for example, turbojet units are installed in huge passenger liners. They differ from the usual ones in the presence of two tanks. One contains the fuel and the other the oxidizer. While a turbojet engine carries only fuel, air blown from the atmosphere is used as an oxidizer.

Turbojet engine

The principle of operation of an aircraft jet engine is based on the same reactive force and the same laws of physics. The most important part is the turbine blades. The final power depends on the size of the blade.

It is thanks to the turbines that the thrust that is needed to accelerate the aircraft is generated. Each of the blades is ten times more powerful than an ordinary automobile internal combustion engine. Turbines are installed after the combustion chamber where the pressure is highest. And the temperature here can reach one and a half thousand degrees.

Double-circuit RD

These units have a lot of advantages over turbojet ones. For example, significantly lower fuel consumption with the same power.

But the engine itself has a more complex design and more weight.

Yes, and the principle of operation of a bypass jet engine is slightly different. The air captured by the turbine is partially compressed and supplied to the first circuit to the compressor and to the second circuit to the fixed blades. The turbine then operates as a low-pressure compressor. In the primary circuit of the engine, the air is compressed and heated, and then, by means of a high-pressure compressor, is supplied to the combustion chamber. This is where the fuel mixes and ignites. Gases are formed that are fed to the high-pressure turbine, due to which the turbine blades rotate, which, in turn, supply rotational motion to the high-pressure compressor. The gases then pass through a low pressure turbine. The latter drives the fan and, finally, the gases get outside, creating traction.

Synchronous taxiways

These are electric motors. The principle of operation of a synchronous reluctance motor is similar to the operation of a stepper unit. Alternating current is applied to the stator and creates a magnetic field around the rotor. The latter rotates due to the fact that it tries to minimize the magnetic resistance. These motors have nothing to do with space exploration and shuttle launches.