How to achieve engine and turbine transmission in passenger aircraft

At a glance, you can see that the landlord does not understand aero engines at all.

Hanging underneath the wings are the engines, which you see as turbines. Actually, you see that it's not a turbine but a fan blade. The turbine is actually one of the components of the gas turbine engine, and several key parts of the gas turbine engine are the intake duct (and fan in the case of turbofan engine), compressor, combustion chamber, turbine nozzle.

The power of the aircraft is completely different from that of the car, and there is no need for transmission at all, because now the engine of the aircraft is the power of the aircraft, and the gas turbine engine produces high-pressure and high-temperature gas in the tail nozzle to continue to expand and accelerate, and is discharged at high speed, generating reaction force to push the aircraft forward. To give you a diagram I hope it will help you understand.

In addition, the civil and aero engines are basically turbofan engines, because the pursuit of civil economy is economic.

That is the engine, the engine burns fuel to promote the turbine rotation, through the synchronous shaft, drive the front fan to rotate, produce a pull, the thrust of the aircraft is the fan pull + the thrust of the tail nozzle to achieve together.

That's the turbofan engine, to put it bluntly, it's the integration of the turbine and the engine, there is a combustion chamber at the back of the turbofan engine, which drives the turbine to rotate by burning kerosene, there are many kinds of engines, don't think that all engines are the same as those in the car, hehe.

Hehe, the upstairs is right, now airliners don't need reciprocating internal combustion engines to drive propellers. Both use fan turbojet engines. The wings are individually owned by engines.

What you see is a fan, a jet engine for an airliner, and it's not all about it. It also relies on the jet flow as thrust.

In fact, the fuel tank of the airliner is also on every engine. The fuselage simply provides ride space and controls.

It is advisable to take a look at the anatomical diagram of the jet engine of the airliner. You'll understand.

The principle of the turbine engine (gas turbine) is the same as that of the Chinese marquee, there is an impeller above the marquee, just like a windmill, when the lamp is lit, the air inside the lamp is heated, and the hot air flow rises to push the impeller above the lamp to rotate, driving the pony below to rotate together.

The gas turbine relies on the high-pressure and high-speed gas generated by the combustion chamber to drive the rotating air of the gas impeller from the air inlet into the gas turbine, and the high-speed rotating compressor compresses the air into high-pressure air. The fuel is burned in the combustion chamber to produce high-temperature and high-pressure air; High temperature and high pressure air expansion pushes the turbine to rotate to do work;

Air is the working medium, the oxygen in the air is the accelerant, and the combustion of fuel makes the air expand to do work, that is, the chemical energy of the fuel is converted into mechanical energy.

1) Propeller: The function is to evenly distribute the air to the compressor.

2) Gear reduction: The function is to reduce the speed of the extremely high-speed shaft to protect the propeller.

3) Compressor: The function is to compress the inhaled air into a high-pressure, high-temperature gas. This process is carried out under adiabatic conditions, so the process is called "isentropic compression".

4) Burner: The function is to burn fuel oil with high-temperature and high-pressure air to produce higher temperature (constant pressure) gas to prepare for the generation of power. Note that there are many burners, which are evenly distributed around the combustion chamber.

5) Turbine: This is the source of power generated by jet engines. It is here that the above-mentioned burning high-temperature and high-pressure gases are converted into kinetic energy (rotational kinetic energy + jet velocity) by cooling and depressurizing.

Among them, the rotational power is mainly to provide power for the propeller, etc., while the power of the aircraft is from the high-speed injection of gas.

In general, the theoretical process consists of four processes: gas, i.e., air is first isentropically compressed, then the fuel is burned to obtain a higher temperature gas, and then isentropic expansion (after powering the aircraft), and the exhaust gases are discharged into the atmosphere.

Turbine engine: It is a form of engine that uses rotating parts to draw kinetic energy from the fluid passing through it, and is a type of internal combustion engine. It is often used as an engine for airplanes and large ships or vehicles.

Working principle: The turbine engine consists of a fan, a low-pressure compressor (unique to the turbofan), a high-pressure compressor, a combustion chamber, a high-pressure turbine to drive the compressor, a low-pressure turbine to drive the fan, and an exhaust system. Among them, the high-pressure compressor, the combustion chamber and the high-pressure turbine are collectively referred to as the core engine, and the available energy in the gas discharged by the core engine is transferred to the low-pressure turbine to drive the fan, and the remaining part is used in the nozzle to accelerate the exhaust gas.

The fan rotor is actually a compressor with long blades of 1 or several stages, and after the air flows through the fan, it is divided into two ways: one is the connotative air flow, the air continues to be compressed by the compressor, and is mixed with fuel in the combustion chamber, the gas expands through the turbine and the nozzle, and the gas is discharged from the tail nozzle at high speed to generate thrust, and the flow distance is through the low-pressure compressor, high-pressure compressor, combustion chamber, high-pressure turbine, low-pressure turbine, and the gas is discharged from the nozzle; The other way is the outer duct airflow, and the air after the fan is directly discharged into the atmosphere through the outer duct or discharged in the nozzle together with the internal gas. Turbofan engines combine the advantages of turbojet and turboprop engines.

The turbofan engine converts most of the gas energy into torque to drive the fan and compressor, and the rest into thrust. The total thrust of a turbofan engine is the sum of the thrust generated by the core engine and the fan.

Hello brothers, it is rare for young people nowadays to have such a traceability of popular science knowledge as you, hehe, I am a relevant practitioner, and I am fully responsible for explaining this problem to you. From the perspective of energy, the principle of a turbine engine is the same as that of a piston engine, which converts the chemical energy of the fuel into heat energy, which is then converted into mechanical motion through a mechanical device. To put it simply, the principle of the turbine engine is to use the heat wave generated by the explosion of aviation kerosene to "blow" the aircraft and make it move, which uses the principle of momentum

m1*v1=m2*v2, i.e., a heat wave of a certain mass of supersonic aircraft mass aircraft speed. That's the rationale.

The basic structure of a turbine engine can be reduced to a cylinder with fan blades at the front and a fan blade at the rear, which are then connected by a shaft. The place between these two fans is where the fuel explodes (the scientific name is the combustion chamber). This formed the basic prototype of a single-rotor turbine engine.

Those two fans plus the connecting shaft are collectively called the rotor. The fan in the direction of the air intake is called a compressor, and its function is to continuously press fresh air into the engine through rotation for explosive fuel. So where does the power for the compressor to rotate come from?

Obviously, the power can only come from the connecting shaft, and the power of the connecting shaft is the fan at the outlet (the scientific name of the fan at the outlet is called the turbine), and the turbine is at the rear of the engine, at the outlet, so the power of its rotation is blown by the air wave, that is, by the air wave.

So the working process of the turbine engine can be described like this, let's push it again: when starting, the turbine engine needs another electric motor or gasoline engine to take it around (you can understand it as the principle of a hand-cranked tractor), and then the combustion chamber begins to inject, ignition, deflagration, the resulting heat wave blows to the turbine, and then the turbine begins to rotate, and at the same time drives the compressor in front to rotate through the connecting shaft, and then the combustion chamber continues to have high-pressure air into the combustion chamber for fuel to continue deflagration, and the cycle repeats. The engine will continue to deflagrate, that is, there will be a continuous heat wave to propel the aircraft (the heat wave will only consume very little energy to propel the turbine, and the remaining energy will still be able to propel the aircraft). Oops, all the phone typing, exhausted....Let's do it first, I don't know if you understand...

The turbofan engine relies on the fan to compress the air into the combustion chamber, and the high-pressure air is mixed with fuel in the combustion chamber and burned to produce high-temperature and high-pressure gas, which is sprayed out from the nozzle to produce huge thrust.

The engine is equivalent to a big fan, blowing wind backwards, and the reaction force of the air naturally makes the plane fly forward, Newton's third law, very simple.

As for the jet engine and fan engine you are talking about, it should be a turbojet engine and a turbofan engine. The main difference between these two engines is the thrust of the **, the turbojet engine has only one duct, its thrust is pure gas, all the air entering the engine is involved in combustion, sprayed backwards, and produces thrust, so it does not have the big fan on the turbofan engine. The thrust of the turbofan engine mainly comes from the large fan at the front, about 70% to 80% of the thrust is generated by it, and the thrust generated by the high-temperature gas coming out of the tail nozzle after combustion accounts for only 20% to 30%.

The air flow channel of the turbofan engine is divided into the inner channel and the outer duct, the air enters the engine from the front intake channel, and the air in the internal channel passes through the low-pressure compressor, and the high-pressure compressor compresses it step by step, enters the combustion chamber, mixes and burns with atomized fuel, and then passes through the high-pressure turbine and low-pressure turbine, and is discharged through the tail nozzle after doing work on the turbine. This part of the air accounts for a very small proportion of the total air intake of the engine, about no more than 30%, so it produces very little thrust and very little. Its main role is to do work on the turbine, the low-pressure turbine drives the low-pressure compressor and the fan through the low-pressure rotor, and the high-pressure turbine drives the high-pressure compressor through the high-pressure rotor to maintain the operation of the engine.

The turbojet engine is simple, it has no outer duct, it is purely suction, combustion, high-speed jetting, and thrust are generated by the compressor. It is precisely because the air sucked in by the turbojet engine is all involved in the combustion, so its fuel consumption is much higher than that of the turbofan engine, but its thrust is also much greater than that of the turbofan engine. Therefore, most of the civil aircraft that consider economy use turbofan engines, while most military aircraft with higher requirements for maneuverability use turbojet engines.

The engine only provides speed, the blades are partially discharged after inhalation, and part of the pressure is mixed with fuel to produce power to make the blades continue to rotate. The wings control the attitude and thus the take-off and landing. The wings can be extended, thus changing the shape of the windward, so that the air velocity above the wings is greater than the air velocity under the wings during takeoff, resulting in a pressure difference between the upper and lower wings, forming a relative vacuum, and the atmospheric pressure will push the aircraft up from under the wings.

A turbine engine is a type of internal combustion engine. It is often used as an engine for aircraft.

According to the different bypass ratios, it is divided into turbofan engine or turbojet engine; In addition, there are turboprop engines (or turboprop engines, turboprop engines, etc.), as well as turboshaft engines similar but used on the turboshaft, as well as gas turbine engines derived from turbine engines for vehicles, ships, power generation, etc.

All turbine engines have three parts: compressor, cumbustion, and turbine. The compressor is usually divided into a low-pressure compressor (low-pressure section) and a high-pressure compressor (high-pressure section), the low-pressure section sometimes also has the effect of an intake fan to increase the air intake, and the incoming airflow is compressed into a high-density, high-pressure, low-speed airflow in the compressor to increase the efficiency of the engine. After the air flow enters the combustion chamber, the fuel is injected from the fuel supply nozzle, which mixes with the gas flow and burns in the combustion chamber.

The high-heat exhaust gases produced after combustion will then push the turbine to rotate, and then carry the remaining energy through the nozzle or exhaust pipe, as for how much energy will be used to propel the turbine, depending on the type and design of the turbine engine, the turbine will be divided into high-pressure and low-pressure sections like compressors.

How aircraft turbine engines work.