How A Gas Turbine (Jet) Engine Works
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- Опубликовано: 13 июл 2014
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The basics of jet engines. Questions? Post to:
jokoengineering
jokoengineeringhelp@gmail.com
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Excellent video. Love to see a fellow left handed that can draw!
This man helped many of us land our part 121/135 job. Thank you
Well done. Thanks for educating us. It helps take away the mystery behind one of the most amazing inventions that enables us to travel at amazing speeds safely.
How have I not found this video before? This has to be one of the best explained videos I have seen on the matter. I guess if you have deep knowledge on a subject you explain it better too.
Awesome! My hard head could never pass this knowledge through until I saw your explanation. Thank you so much
This is the best description of Gas Turbine ever !
Napasorn Narod 9
Excellent video...I'm new to the material handling industry and this gives me a great overview of turbine blades...thanks!
THANK YOU JOKO THE ENGINEER!!!
Thank you, you thought me a lot about Jet Turbine Engine. Have a nice day !
you are so good,I had never understood jet engines by the time watching the your videos.thanks
That's a beautiful fan! Thank you for the wonderful explanation.
Very well done thanks for the effort helped me a lot
very simple way of explanation on a complex task!!!!
That was an excellent description.
great great job.The very best because it's so simple and even a lay man like me can understand.Thank you!
Perfect. This is better than any animation.
At last...I understand and visualize the concept. Thank you
That gets a subscribe. Looking foward to watching more of your vids. Very good explanation. Now back to reading the jet engine chapter of Exactly.
Thanks for the inside very well explained.
ol vid. Even though i could not understand every word I feel like I've learnt much. Thank you very much.
Great job! Thank you for sharing this....
Thank you for the excellent lecture..it's helps a lot.
Excellent explanation, I have learnt something
Still a favorite after all these years. :-)
Very descriptive!
Aaah! That is why its called afterburner =D
Many thanks! That was really helpful.
Excellent job!
Nice fish shadow puppet at the beginning! ☺ and turbine lecture😊
Thank you for this video great work !!
Great video. I love turbine engines!
Awesome video... very good explanation.. helped me a lot!!!! cheers bro!!!!
great explaination , thanks
Thank you for the vid Sir.
Thank you Team
Very helpful, thank you
Good illustration..
Very nice video it helped a lot thank u
nice vid, well made
Thanks a lot 👍 that was extremely helpful 💪
Very helpful!
very informative, thank you :D
I finally understood, thank you
Thx bro I hope u still teaching us 😘😘😘
good explanation!
Thanks, Glad I could help
SilboMovies yes
You don’t need afterburner to break the sound barrier. I know it’s a short list of the most modern fighter jets. A.k.a Super-Cruise, really the topic for a different video altogether.
excellent explanation...
+Maneer Alam
Thanks
You described a process I could barely processed let alone describe it.
Thank you !!!
Thanks a lot brother! Helped me a lot. :)
+Harikrishnan Nair
My Pleasure thank you for watching.
Thank you
The best and simple explaination on turbine for me.. thanks alot..
Good job. Remember though, some military engines are high bypass. You're referring to fighter aircraft. Cargo aircraft are also high bypass engines, like the one you described here.
Thanks a lot~!
Thanks for a cool video and for reminding me why I have a mac :P
+Mr_Good_Will
My girlfriend uses a mac and we end up teasing each other all the time. Thanks for the comment!
tnx bro, that helped me a lot :)
Marco quemasda
Glad to be of help!
I can hardly believe someone thought about and invented these engines! They seem so complicated!
hart strings - Sir Frank Whittle
Thanks
Complex mechanism ... simple explanation
Avishek Purkayastha - simple mechanism (one rotating part) complex physics.
Well done!!!!!!!!!!!!!1
i love this!
Great name
It IS a beautiful fan.
Are there 2 fuel inlets in fighter plane engines one between compressor and turbine and the other after turbine?
The intake fans provide thrust?
Good vid, but I don’t believe you gave very good explanation of the Stator blades and the important part they play and how they work, and I have seen this in many YT vids where ppl try to build a turbo jet engine type, negating to include properly formed Stators which redirect the air onto the next stage increasing angular deflection of the airflow onto the following blades for a greater torque increase against the turbine blades of each stage.
I’m only a novice, but I believe this is the purpose , reason and need of the Stator vanes, often misunderstood, overlooked and/or understated in the explanation of turbine/jet engines design.
Anyone , please correct me and explain if I am wrong. Nice vid, Thanks for sharing.
I have a question. How the propeller or the main shaft get rotation power. Is there any electric motor work to give the rotation power?
Thanks for your video. Please tell how do the front blades get power to rotate initialy before the combustion starts.
There is a small engine in the back of commercial jets (the auxillary power unit or APU) that provides the electrical energy required to start the blades spinning and igniting the fuel.
Do you have more A&P type videos like this? Great breakdown.
Thanks. I have this one: ruclips.net/video/ipvAYcy1h1w/видео.html
thanxxxxx
Great explanation! Thanks. Approximately how many rpm does the Turbo fan spin.? if one removes the turbines behind the combusting chamber and is able to turn the fan in the front by some other means (external from the jet ), will there be more thrust produced due to no energy lost by the exhaust gas in turning the turbines?
Turbofans are linked on the same shaft as the turbines which are powered by the accelarating exhaust gas. The turbines takes up some of the energy to torque the large fan. Newer turbofans use less turbines and include a gearbox to reduce the fan speed lower to subsonic levels at the wingtip. There should be more thrust produced due to the greater ratio of the intake air (slower) and the exit air. I stand for correction on this
Small criticism, a compression stage isn't one row of blades, its a rotor-stator pair. Good video otherwise, keep up the good work
Is that the flight moves by pull or push. Confused. I believe it's by mainly by pull...
Quick question!
When advancing the throttle, does it increase the rotating speed of the fan blades or does it just increase the amount of fuel injected?
Since the rotating speed of the fan blades relies on the turbine, and therefore the air moving out, the more fuel the faster air moves, and the quicker the turbine will spin therefore increasing fan speed. I believe after a certain amount of fuel though, the mixture of fuel to air will become too high and you will experience a flameout. I'm no expert though
Where are the injectors on the diagram/picture you’ve used?
great video. ... but i wish it had some more information including the energy specifications, differences with and without afterburner and so... Anyway, better than other stuff available .
MoNika .Mondal Many thanks. I currently have some information on compressor and turbine calculations if that's the kind of energy you're looking for. You can find one here, the same math applies to compressors.
ruclips.net/video/RoTVeF13HDc/видео.html
If that's not helpful, are you looking for more general specifications rather than calculation?
Well illustrated ...
Pradeep Kumar Many thanks
tks a lot. may you send me some document about A320.A321
So this engine is what they call the Turbofan jet engine, since the front fan is what generates almost all the thrust. So the fan also stuffs air into the compressor too I imagine. About how many PSI does the fan provide at the front of the compressor opening when the engine is at full throttle? Very interesting.
So then I suppose the 8 engines on the B-52 bomber are pure jet engines that use the exhaust for its thrust. I love the sound of the B-52 on takeoff. Good info. Thanks
Typically it'd be characterized as the fan pressure ratio, which is the ratio of the stagnation pressure before and after the fan. The stagnation pressure is the pressure if you brought the flow to rest - it's nice because it provides a measurement of the change in overall flow energy. For a high-bypass turbofan in cruise condition it's somewhere around 1.5-1.6, so the stagnation pressure after the fan is about 50% higher. For the ultra-high bypass ratio turbofans such as the PW1100G on A320neo, it's a bit lower (1.3-1.4 or so) because the fan thrust is from moving more air rather than accelerating that air faster.
so the engine is taking in cool air and compressing it and ejecting hot air,and that creates thrust(without using the afterburner?) ...so why do we even need fuel in the jet engines(if we don't want to use afterburner)? to rotate the rotors?
Thanks for explaining I always thought the afterburner put fuel into the turbine not the exhaust gasses.
No. And also the afterburner is not a critical part to making a fast fighter aircraft it is jus used in times when fast acceleration is needed e.g. takeoff and emergencies
This is the same for Trent 2000's, right?
To clear my confusion, when the engine starts up cold, does the compressor first spin to compress the air to send to the turbines? you also mentioned that the turbine is spinning the compressor as well.
It depends on the engine. Some engines have a built in smaller "starter" that spins the compressor quickly enough for it to build compression and ignite the fuel. Smaller engines utilize an external blower, which blows air through the front to spin the compressor until ignition occurs.
@@JokoEngineeringhelp thanks. that clears it up.
As the combustion of the air/fuel mixture presses outward against the turbine blades in the rear of the engine, how come it does not press equally against the blades forcing air into the combustion chamber? It would seem that the two turbines would be fighting one another and the energy output would be nil. Of course jet engines work well, but how is this back pressure problem overcome?
How does the gas turbine engine on the M1A2 Abrams?
I still do not understand why does the exhaust air not go backwards. Can you please explain to me?
Wouldn't the after burn cause the turbine blades to spin backwards? It sounds like the afterburner would be higher pressure than the air that just passed through the turbine from the combustion chamber.
But, the surrounding air (behind the engine nozzle) is at still lower pressure. So, the gases in the afterburner prefer to flow in that direction.
Actually fuel pumped into the exaust doesn't automatically ignite. They locate an igniter back there.
I used to sleep in the front of those engines in the Military on guard duty. The wind turn those fans and they would tick tick tick tick you right to sleep lol
suooppper sir
Ok. Heres a question that Ive yet to get an answer for and Ill bet you can answer it.
The hot air expanding makes the pressure which gives thrust, right? So, if that pressure is greater than the gas mixture before it is ignited, what keeps that greater pressure from blowing back into the compressor?
Great question. When flow through the compressor is abnormal you would call that compressor stall or compressor surge. Here is an example:
ruclips.net/video/advmGVR5Nkw/видео.html
Usually the pressure on one end of the turbines and the lack of pressure on the other end of the turbines causes a stable flow to the end that has no pressure
To expand a bit (like the gas), the pressure increases through the compressor, slightly decreases through the burner, then significantly decreases through the turbine. The only place it increases is the compressor where work is being done on the flow.
so if the turbine powers the fan and the compressor, how does it get started? I mean when the engine is off and the fan is not rating, how does the turbine get started to power the fan and the compressors?
+Dave0551
Gas turbine engines are generally started by high pressure air entering the engine from a separate "Start Cart" or JSF (Jet fuel starter). A start cart is not part of the aircraft while a jet fuel starter is integrated into the aircraft. Both supply pressurized air adequate to move the rotating parts of the engine fast enough to rotate on its own when ignition is introduced in the combustors.
Joko Engineeringhelp so in more simple words, its a high pressured air that enters the turbine to get the parts moving?
Dave0551
Exactly!
+Dave0551 - depends on the gas turbine design and intended service....industrial machines are rotated to lightoff speed with a starter motor (electric, air, or hydraulic) connected via the accessory gear assembly. Biger machines may have an inching or jogging helper motor in addition for controlled cool down.
+Dave0551 Thanks for asking that question Dave. I've searched countless videos that ignore this very basic and logical "chicken-or-egg" starting point. Everyone seems to want to impart their knowledge of jet engines with monotonous sameness, all leaving out this important information. Well done mate.
Rolls Royce uses carbon composite blade fans on they’re new engines.
Mr. Engineer, I am very interested in jet engine engineering. I want to learn from you. You will help me.
nice video, but how by pass air provide 75% of the thrust? the engine only provide 25%?
Dabulous, on a turbofan engine, the inner core that is taking 25% of the air flow is there almost exclusively to power the fan. So it's job is not to provide thrust, even if it does anyway, but to provide the drive for the fan. And the thrust of a jet engine is a force that is pushing forward, not backward as most people think.
No Arsian, it's not that way.
As you know this is a turbo shaft engine in base and coverted to turbo fan engine
and turbo shaft eng.duty is to rotate shaft only and it rotate a rotor for flying.
In this engine a fan is located in front of it and the fan is engaged to the power turbine and P/T drive the fan in order to move a large volume of air from the front to back of the engine and it cause to obtain thrust
What were those gears for?
For the accessory drive to drive the fuel pump, oil pump and the other stuff.
There are two types of compressors: 1) Centrifugal 2) Axial-flow. You were combining the terms Centrifugal and Axial, which I don't think is correct. And if anything, a Centrifugal compressor has a radial effect on the air, not an axial effect. And a Axial-flow compressor has an axial effect on the air. So, I wouldn't use the term Centrifugal and Axial together to mean the same thing. Unless I'm missing something.
I found a reference in the Jeppesen Powerplant Textbook, page 3-13: " The centrifugal compresor, sometimes called a radial outflow compressor, is one of the earliestr compressor designs and is still used today..."
if the air gets very hot at 450 degress with the compressors, can water be just the fuel as it will be instantly vaporized and will turn to steam
Yes, however you would need something to keep heating the water or the water will cool the system down very quickly as it takes a lot of energy to turn water to steam. Nice idea.
i know this a stupid question but will it work vertical???
can i just put an electric fan on top of it to start it???stupid just learning now
It can function in the vertical position, I imagine it would be quite tricky to get something to fly with a vertical gas turbine engine though. They have external fans used for starting, some are equipped with a starter.
Check the “Flyboard”, it uses compact jet engines in a vertical setup to hover.
fucking awesome video!
So turbines provides the rotating energy ? Right
How initially the engine begin to rotate with out the compression of air
It depends on the engine. Sometimes an onboard starter, sometimes external.
good explanation, but you could work on the mics that you're using, the volume changing everytime is very uncomfortable
Can someone explain how does it compress air? I mean how does it generate pressure, are the blades spinning at different velocity?
The pitch of the rotor blade stages increase while the area available for the airflow gets smaller.
increasing the number of blades progressively also aids in compression. yes if the area for the compression gets larger or smaller towards the combustion chamber then the velocity increases or decreases with a change in its diameter.
So it is basically being pushed towards a progressively smaller area, right?
Not really. In your statement a fixed or CONSTANT AIR volume of air is pushed towards progressively smaller area (actually volume). In the jet engine it really is an INCREASE in air volume into a fixed containing volume. I will try to explain. Assume we first close off the compressor stage from the combustion chamber. Now we allow air to be sucked in by the first forward compressor ring. we immediately close up the intake just forward of this compressor blade ring so no more air is allowed in. We also blocked any air from entering the combustion chamber aft of the compressor stage. So we have a sealed compressor stage area (volume)
Prior to this air being sucked in there was air already in this compressor stage volume of 1 atmosphere. The compressor stage volume is constant, it does not change like that of a piston engine that compresses air by reducing the volume of the chamber (being pushed towards a progressively smaller area). the volume between the first compressor blade ring and the last ring is constant. The compressor blades are turning but they do not change the volume within its housing. What happens is the spinning force of the blades pushes the air from the front towards the back of the engine. What will happen in this scenario where we blocked any further incoming air and closed off the combustion chamber from the compressor, is the newly let air in prior to blocking off the intake is forced into this fixed volume (sealed off compressor stage volume). The newer intake air will mix with the air already inside of the compressor stage and increas the pressure to higher than one bar. This new air mixture will come int equilibrium. Note the volume of containing space is the same, but the density and mass of the air is higher. In your statement the volume of containing space is reduced with the mass of air constant.
I hope my explanation is good