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But she is going to be a long bird. Look at it from that way. The body should taper in eventually.From side angle, it seems the TFX will have a large body structure unlike the mock-up that is constantly on display.
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IRST in front of the cockpit and EOTS at the bottom. Both are designed with stealth radomes.
There probably will beI hope this will have a system like DAS and not just an EOTS.
I hope this will have a system like DAS and not just an EOTS.
It is missing the cockpit. The architecture is still not finalized. Many things will change until the critical design review.
Just like how @Nilgiri or @Yasar and others have pointed out, things are not that simple. Also, context is important when you quote or cite external sources. In the video you've linked, Mahmut Akşit says that the (single crystal turbine blades) could potentially withstand temperatures of 1500K, even up to 1800K if you apply all the necessary measures (I'm not native Turkish so I've understood that wrongly, but that's what I've found by translating it). That is the important context here. As he states, those "necessary measures" range from more advanced ceramic coatings to more advanced cooling channels. You keep insisting :Here source eat this and shut up. He literally says 1500-1800 degrees kelvin. Tubitak's director mentioned 1400 degrees Celcius but Tubitak gives that value for the blades they produced and delivered before TEI treated the blades with their own processes.
By the way, STG 1 means stage 1 power turbine, and STG 2 means stage 2
Stage 1 is where those little dent cooling channels are needed because stage 2 has a lower temperature so those are not needed. And he mentions ceramic thermal barrier coating and new more advanced coatings are being studied. There is enough evidence that current SX blades will be enough up to 1600 degrees Celcius.
but it's not simple to just scale things up and hope for it to work. You mention "better cooling channels" just like what Akşit mentions, but when a turbine blade has a different cooling channel design, that makes it a fundamentally different turbine blade in the first place. It's not something casual as just get an existing design and drill some holes on it, no. For instance, depending on who you ask, it took the leading edge industries a decade or two to get to film cooling designs from simple internal cooling designs. Now I'm not saying that it's gonna take that long for Türkiye since you guys are playing a catch up, but that draws an understandable picture that it's not a simple matter.current single crystal blades will (not) have any problems up to ~1600 degrees celsius when used in a turbofan engine.
Maybe you can tell me just for the drilling process, how many failures happened at pratt for it (when we establish innovate something here)....how many engineers have had to revisit it in the RnD tiers.
The crack initiation points and achieving quality control with that.
If its so easily scaled, the Russian (And Chinese) engines (simply going upon single crystal + temperature soundbite) would have same TBO and MRO reliability/assurance as West by now surely? What is the stage of their capital machinery research? What are the costs and efficiencies?
First of al you need to learn to be polite when you post. Offensive language has no place in our forum. For that I am afraid you have earned yourself a warning.Here source eat this and shut up. He literally says 1500-1800 degrees kelvin. Tubitak's director mentioned 1400 degrees Celcius but Tubitak gives that value for the blades they produced and delivered before TEI treated the blades with their own processes.
By the way, STG 1 means stage 1 power turbine, and STG 2 means stage 2
Stage 1 is where those little dent cooling channels are needed because stage 2 has a lower temperature so those are not needed. And he mentions ceramic thermal barrier coating and new more advanced coatings are being studied. There is enough evidence that current SX blades will be enough up to 1600 degrees Celcius.
I know there's a program called BEOS which will have M/LWIR MCT imaging sensors, but is BEOS a DAS-like system(ie. MAWS) or EOTS-like system(ie. conformal targeting pod)?Ther will be a sensor covering 360 degrees, in a interview with Ismail Demir told that Tubitak is working on that.
BEOS is EOTS like. M/LWIR sensors are for DAS like system AFAIK.I know there's a program called BEOS which will have M/LWIR MCT imaging sensors, but is BEOS a DAS-like system(ie. MAWS) or EOTS-like system(ie. conformal targeting pod)?
A warning! Right now, I think you're over-expecting. But inside there is chaos. I recommend that you do not expect too much.It is missing the cockpit. The architecture is still not finalized. Many things will change until the critical design review.
I think we should tread lightly about exporting TFX. There are so many variables to consider before we hand the most strategic weapon we have to other countries(excluding Azerbaijan).Most likely Pakistan and Azerbaijan will be the first customers of TFX as well. It seems they are interested in Kizilelma too. There will be a twin seat and export variant developments in TFX and since the priority is in Turkish Air Forces, it will take the 2035s to be able to sell to TFX-Int for markets. There are many countries that are looking forward to the aviation projects that Turkey is developing.
First of al you need to learn to be polite when you post. Offensive language has no place in our forum. For that I am afraid you have earned yourself a warning.
Secondly you need to listen to Dr Aksit’s words carefully. He doesn’t say anything contrary to what I have been saying. He clearly says the high pressure blades are going to have special air channels to be cut in to them and air blown to cool them. Also he clearly says that these are blades that have not yet been covered with heat resistant finish. They will be covered with that finish before being used. Not as you claimed they would be used as they were. But in this post you seem to have changed your views a little. Which means you are learning.
1400Kelvin = 1124 degrees Celsius
1800Kelvin = 1527 degrees Celsius.
He says they have an operational range between these two temperatures. You never operate at your top limit.
So from engineers’ point of view we are looking at 1327 degrees Celsius operational temperatures. So previous comments about turbine entry temperatures of 1400Celsius still stands.
But to have blades that can withstand up to 1500degrees Celsius are very encouraging. However as the size of blades increase there will be more difficulties.
Turbine section of TS1400 is made out of 2 stages:
1 x High pressure turbine stage (Stg1) : air cooling and heat resistant ceramic finish
1 x Low pressure turbine stage (Stg2) must have special surface finish to stop corrosion.
In engineering we call them turbine stages. Now you know them too.
I think we should tread lightly about exporting TFX. There are so many variables to consider before we hand the most strategic weapon we have to other countries(excluding Azerbaijan).
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Sore losers are at it again!
Honestly if I were Greek, I would genuinely feel ashamed...