TR Propulsion Systems

[Radonsider]

Mr Akşit: "It's not the 35000lb thrust level that will challenge us in MmU's engine. We are confident that we will reach this level. There are some new technologies that will challenge us in MMU engine such as Coverging Diverging nozzle technology that we are currently working on. Since the MMU engine is a new generation engine, it must be stealth"

Thanks tolgaözbek.com

What I catched is he says "Radar stealth" and Tolga Özbek adds "IR stealth".

So they are working for a serrated nozzle or F-22 like nozzle?

 

[Cabatli_TR]

According to information received by Mr T. Özbek, TF10000 (3,5m length) will have moving nozzle technology (TVC?) as well.

 

[Radonsider]

According to information received by Mr T. Özbek, TF10000 (3,5m length) will have moving nozzle technology (TVC) as well.

Pardon me but can you give link or something else for that, I will share this but I need the source

 

[Zafer]

If the source of the information is Mr Akşit's talk that Tolga Özbek shared, Mr Akşit told about a converging diverging nozzle similar to I guess an F16 nozzle which is not vectored thrust.

 

[Cabatli_TR]

Pardon me but can you give link or something else for that, I will share this but I need the source

https://twitter.com/i/web/status/1565442216084078592

 

[Radonsider]

https://twitter.com/i/web/status/1565442216084078592

Thanks

 

[Cabatli_TR]

If the source of the information is Mr Akşit's talk that Tolga Özbek shared, Mr Akşit told about a converging diverging nozzle similar to I guess an F16 nozzle which is not vectored thrust.

Since this project aims to develop technology and preparation for the MMU engine, it is possible that such systems can be experimentally developed on this engine or it may be just moving nozzle technology that F110 have that will be used only to increase thrust.

 

[Huelague]

What I catched is he says "Radar stealth" and Tolga Özbek adds "IR stealth".

So they are working for a serrated nozzle or F-22 like nozzle?

Thats what I said multiple times to Mr. Aksit

 

[Radonsider]

Thats what I said multiple times to Mr. Aksit

So TF-X going to be more sexy

 

[Fighter_35]

https://twitter.com/i/web/status/1565442216084078592

Hareketli nozzle is not TVC nozzle. Hareketli nozzle means ,it can change its area like f-16 nozzle

 

[Brokengineer]

The point mr Aksit empahised is tf6000 will already be a f110 miniature 4th gen engine. Once enough data acquired, it will be combined with 5th gen technology in a larger core which is going to be used in tfx

 

[Cabatli_TR]

The point mr Aksit empahised is tf6000 will already be a f110 miniature 4th gen engine. Once enough data acquired, it will be combined with 5th gen technology in a larger core which is going to be used in tfx

What is required from a 5th generation engine

• Lower Noise
• Lower IR signature
• Lower RCS nozzle
• Low By-pass ratio
• Supercruise
• Powerful electricity generation

 

[Zafer]

Low By-pass ratio

I don't see where this comes from.
Low compared to what.

 

[Merzifonlu]

Low by-pass ratio? Are you sure, Sir?

 

[Fighter_35]

Of course low by pass ratio?? What do you think low by pass means??
In order to go in supersonic, it should have low by pass ratio unlike civilian passenger aircaraft turbo fans which need to be more efficient, silent and slow!! All fighter aircraft engines which operates above mach1 are low by pass turbofan . Low by pass means , it has low air going through the fans than the air through the compressor part.

 

[Yasar_TR]

Just because the bypass ratio of TF-6000 is 1.08 and not 0.5 doesn‘t make it high bypass ratio engine. Yes it has more air going around the engine than similarly powered military jet engines. But it is still low bypass. In order to qualify as a high bypass engine ratio, the ratio needs to be in excess of 3 or4 ; (More likely 8 or 10 in fact as it is in commercial passenger planes.)
Quite likely that they wanted to suppress the heat signature of the nozzle with more air flow or lower the noise level a bit more and maybe to get more fuel economy. Or all of the above!
RR Pearl class engines with a bypass ratio of around 3.5 to 5 fly transonic. So that sort of bypass ratio doesn’t stop it going supersonic.

 

[Bogeyman]

https://twitter.com/i/web/status/1542969197055168512

Prof. Dr. İsmail DEMİR: "TÜBİTAK-SAGE is working in the field of hypersonic missiles."

We can now say that Tübitak SAGE has performed the ignition of the first scramjet engine prototype.

https://twitter.com/i/web/status/1565673498974064643

Gürcan Okumuş implied that they tested the ramjet engine in hypersonic speed regimes.

Well, we already announced this months ago. Those who were following me closely understood the matter immediately.

 

[Cabatli_TR]

Low by-pass ratio? Are you sure, Sir?

Ofcourse! If you are planning a quieter, cost-effective (fuel saving) and environmentally friendly subsonic flight by filling large fan of your turbofan engine with plenty of air, you will make your engine HBP. The air intakes is wider in them so the Fan fills with very strong air and the turbine together performs the desired function and thrust.

But if you say that I will absorb relatively small amount of air (compared ro HBP) with fans, compress it in compressors, heat it and burn it with dense fuel in the turbines and in this way, I will get a very strong thrust then you should make a LBP turbofan. High noise, intense fuel consumption are characteristic of this type of engine but if you want to fly aircraft at supersonic speeds, those are conditions that you have to endure.

 

[Fighter_35]

https://twitter.com/i/web/status/1565673498974064643

Gürcan Okumuş implied that they tested the ramjet engine in hypersonic speed regimes.

Well, we already announced this months ago. Those who were following me closely understood the matter immediately.

Nope, today almost every important o e tweets one word . Taht is why he tweeted this ,not because they made test or anything like that

 

[Pilatino]

What about DSI and Thrust Vectoring? Should we expect the best tech for the TFX