TR Propulsion Systems

[uçuyorum]

These are arbitrary numbers. It all depends on how well your cooling processes are applied and how good your ceramic coating is. Russian AL41 class engines use Directionally Solidified blades (NOT single crystal) but achieve a TIT of 1645+ degrees Celsius. Even as high as 1700 degrees Celsius is quoted. To achieve nearly 20000lbf dry 35000 wet thrust.

But for how long

 

[Yasar_TR]

But for how long

That is why we and most Western engine manufacturers use single crystal turbine blades. They last longer. Because the creep degradation sets in much slower.

But the high inlet temperature is not only specific to engines employing single crystal blades. Yet It is easier to attain higher TIT values with single crystals. But just with single crystal blades the engine parts would still melt if not cooled and ceramic coating applied. Better crystals means higher top temperature threshold with cooling and coating. So they are interdependent on each other in a way.

 

[Nilgiri]

That is why we and most Western engine manufacturers use single crystal turbine blades. They last longer. Because the creep degradation sets in much slower.

But the high inlet temperature is not only specific to engines employing single crystal blades. Yet It is easier to attain higher TIT values with single crystals. But just with single crystal blades the engine parts would still melt if not cooled and ceramic coating applied. Better crystals means higher top temperature threshold with cooling and coating. So they are interdependent on each other in a way.

It really boils down to the normal distribution vis a vis the factor(s) you are changing.

Old post i plot the normal distribution conceptually: https://defencehub.live/threads/propulsion-systems.3/page-57#post-111270

So if you keep some relevant TIT the same between:

- S(X) (newest/best),
- DS(X) (intermediate)
- Non-DS(X) (oldest/worst)

and then apply exact same cooling mitigations, manufacturing quality, design etc.... i.e hold everything else ceterus paribus in this multivariate situation and only play with grain boundary prevalence (where S(X) achieves as "n=0", DS(X) as "small n" and non-DS(X) as "high n")

...you will get three different normal distributions on their failures commensurate to their grain boundary prevalence (and thus problem initiation + growth rate, all of which contribute to the normal distribution position w.r.t time).

Similarly if you keep S(X) the same alongside cooling....you can now use TIT as the factor to change (to increase it, take a hit on the normal distribution spread and see where the tradeoff is now optimal w.r.t some red line you have for the X% failure rate you set).

i.e for each failure rate, the TIT (required to cause it with same amount of time seen) will be higher for S(X) relative to DS(X) etc.

 

[Bogeyman]

Single crystal wing types and generational differences

https://www.metalurji.org.tr/dergi/dergi169/d169_3039.pdf

@TheInsider @Yasar

Here are some illustrative images related to single-crystal turbines.

 

[Bogeyman]

https://twitter.com/i/web/status/2051646295513661897

A turbofan engine developed by the Ministry of National Defense R&D Center, capable of producing 42,000 lbf of power.

 

[Padronsoalo]

 

[Zafer]

View attachment 80369

465 in typo spotted, its is 46,5 in instead

 

[Zafer]

I am guessing the MSB Arge engine is one of TEI early TF35k builds. Nobody makes a metal engine as a show display piece.

@ErayGüçlüer

 

[Sanchez]

I am guessing the MSB Arge engine is one of TEI early TF35k builds. Nobody makes a metal engine as a show display piece.

@ErayGüçlüer

MSB Arge would. Fishy.

 

[SCAR]

I am guessing the MSB Arge engine is one of TEI early TF35k builds. Nobody makes a metal engine as a show display piece.

@ErayGüçlüer

Eray Güçlüer??? Come on @Zafer here is Defencehub, not Defenceturk bs forum

 

[Sanchez]

But we had very nice news today as well.

Subcontractor deals were signed today between TRMotor and TAI, İDAK, HARPAX, ANOVA, ALP Aviation, TAAC, and PCS Test and Automation for TF35K.

https://twitter.com/i/web/status/2051704201625874462

 

[TR_123456]

There is another one

- Our ONUR TURBO SHAFT HELICOPTER ENGINE, all of whose turbine and parts are again produced by our R&D

https://twitter.com/i/web/status/2051728092935213133

Wtf is going on,why are they doing this?

 

[Bogeyman]

Wtf is going on,why are they doing this?

They want you to have a heart attack, what other reason would there be?

 

[uçuyorum]

https://twitter.com/i/web/status/2051687650705158611

 

[Huelague]

Not really related to topic, are our facilities, employees and centers well protected? Not only in peace times.

 

[Pokemonte13]

Not really related to topic, are our facilities, employees and centers well protected? Not only in peace times.

no

 

[BalkanTurk90]

The MSB Arge turbofan engine looks like real engine not mockup or some plastic just for show , if u look closse u can see how real it looks ! And perhaps they build it fast because its reverse engenering of US engines like f110 and not design from strach like tf 35000 which will be the best and its lifespan alot better !

 

[Sanchez]

There is another one

- Our ONUR TURBO SHAFT HELICOPTER ENGINE, all of whose turbine and parts are again produced by our R&D

https://twitter.com/i/web/status/2051728092935213133

Again, fishy.

 

[Pokemonte13]

At this speed MSB arge will present their 7th generation fighter at IDEF 2027

 

[Merzifonlu]

Here we go.

Again, fishy.

Very fishy.