TR Propulsion Systems

[Oublious]

3700?

I can not remember that.

 

[Trakya_forever]

Yep KTJ 3700 for Kara Atmaca. Maybe later for Som and Atmaca as well because it has the same diameter with 3200.

 

[Afif]

For those who would like to understand it in simpler form:
In a turbofan (bypass) engine, the bypass ratio is a comparison between the mass flow rate of air drawn into the engine through the fan disk that goes around the engine core with the mass flow rate of the air that goes through the engine core. In an engine with a bypass ration of 10:1, for every 11 units of air drawn into the engine, 10 will bypass the engine core and 1 will go through it.
In short for every 10 parts of air thrown out by the main fan 1 part of air goes through the engine burning the fuel and thrown out of the nozzle.
This is the normal type of operation one would see in a passenger planes’ turbofan engine.
But in an engine like F110 which has a by pass ratio of 0.76:1;
for every 0.76 part of air thrown out by the main fan, 1 part of air is used in the burning of fuel andthrown out of the nozzle.
So if the by pass ratio of TF6000 is 1.08 , then for every 1.08 part of air thrown out by the main fan, 1 unit of air goes through the engine’s hot parts.
This makes the TF6000 engine a little higher by pass than an engine like f110. But not a high by pass engine like the ones we would see in jet liners where around 90% of thrust is provided by the air thrown out around the engine by the big fan.
Both RR Turbomeca and Honeywell F125 have lower by pass ratios than TF6000. Higher bypass engines are quieter and more suitable to stealth operations. Technology used on engines like RR Pearl with higher by pass ratios are being used for the basis on which the tempest engine is being produced.

Are turbine blisk ( I mean disk and the single crystal blade ) are same as it is in ts1400? I am just little confused! Because, the similer class f124 engine has turbine inlet temperature of 1350c. But as far I remember the blades that are developed by tubitak mam withstand up to 1500k ( which mean 1226c only )

 

[Yasar_TR]

Are turbine blisk ( I mean disk and the single crystal blade ) are same as it is in ts1400? I am just little confused! Because, the similer class f124 engine has turbine inlet temperature of 1350c. But as far I remember the blades that are developed by tubitak mam withstand up to 1500k ( which mean 1226c only )

Some modern engines have blisk construction in their compressor fans. A blisk is in an aeroengine component that consists of a rotor disk and multiple blades in a single unitary part.
The f110GE132 (aka F110GE129EFE) has blisk fan blades. TEI is capable of producing these. TEI MD Dr. Aksit has reiterated many times that they can.
RR, in Pearl engine have produced blisks in their HP compressor section as well. So do MTU in EJ200.
There are shroudless HP turbines being produced. But never heard of turbine blisks.
TS-1400 uses single crystal blades in the turbine section. The turbine inlet temperature of TS-1400 is not above 1350 - 1400 degrees Celsius. The HP turbine blades of this engine is capable of withstanding these temperatures and more. Dr Aksit had mentioned in excess of 1450 degrees Celsius. (He even said something about withstanding temperatures reaching 1500 degrees Celsius at the turbine in let) Infact TEI can manufacture single crystal turbine blades suitable for F110. (Again Dr Aksit’s words - he Infact, specifically said that they can manufacture an engine as powerful as F119 that propels F22 Raptor)

 

[Afif]

Some modern engines have blisk construction in their compressor fans. A blisk is in an aeroengine component that consists of a rotor disk and multiple blades in a single unitary part.
The f110GE132 (aka F110GE129EFE) has blisk fan blades. TEI is capable of producing these. TEI MD Dr. Aksit has reiterated many times that they can.
RR, in Pearl engine have produced blisks in their HP compressor section as well. So do MTU in EJ200.
There are shroudless HP turbines being produced. But never heard of turbine blisks.
TS-1400 uses single crystal blades in the turbine section. The turbine inlet temperature of TS-1400 is not above 1350 - 1400 degrees Celsius. The HP turbine blades of this engine is capable of withstanding these temperatures and more. Dr Aksit had mentioned in excess of 1450 degrees Celsius. (He even said something about withstanding temperatures reaching 1500 degrees Celsius at the turbine in let) Infact TEI can manufacture single crystal turbine blades suitable for F110. (Again Dr Aksit’s words - he Infact, specifically said that they can manufacture an engine as powerful as F119 that propels F22 Raptor)

Like high pressure compressor turbine also contains similer two parts ( blade and disk ) people just call 'turbine blisk' simply 'TURBINE'. I knew that, TEI manufactures the compressor blisk for F110. However, I didn't knew that they can even manufacturer the suitable turbine blades for F110 too ( as you quoted Dr. Aksit .) Usually turboshaft inlet temp doesn't exceed the 1000 c. For example kilmov tv3-117 engine that are going to be used on atak ii only has turbine inlet temperature up to 990 c. It is the turbofans that's really has high inlet temp. Any way, can you tell me if TUSAS, TEI or TUBITAK will participate in upcoming teknefest 2022 ? Is it as big as IDEF? Is there a chance TEI will unveil the first prototype of the TF6000 there?

 

[Yasar_TR]

people just call 'turbine blisk' simply 'TURBINE'.

Iam afraid, people that know what they are talking about, don’t.
“BLISK” means a SINGLE PART that consist of blades and the rotor that normally house them all produced as a single unit.
Turbines, if using blades that are Directionally Solidified or Single Crystal are not manufactured as blisk. They are separate units. These blades are individually slotted in to the rotor housing. I don’t know of a technology where a single unit of crystal can be cast that forms both blades and the rotor.

 

[Afif]

Iam afraid, people that know what they are talking about, don’t.
“BLISK” means a SINGLE PART that consist of blades and the rotor that normally house them all produced as a single unit.
Turbines, if using blades that are Directionally Solidified or Single Crystal are not manufactured as blisk. They are separate units. These blades are individually slotted in to the rotor housing. I don’t know of a technology where a single unit of crystal can be cast that forms both blades and the rotor.

Yeah! I know that, unlike compressor turbine's disk and single crystal blades are manufacturer separately and then blades are slotted in the disk. However, after it become integrated in one piece you can still ' technically' call it a 'blisk'. But it is avoided for not to be confused with compressor blisk (which unlike turbine, manufactured from the very beginning in 'SINGLE PART' with blades are blended in the disk )

 

[Nilgiri]

after it become integrated in one piece you can still ' technically' call it a 'blisk'.

No blisk purely refers to it being permanently integrally made (i.e blades + disk in one entire piece at the end, i.e the blades can no longer be individually removed).

If you slot blades in (and you can remove them separately afterwards too for say maintenance), that is just a regular compressor or turbine rotor. You cannot use blisk to describe that.

Blisk would need its entire removal and replacement for say maintenance (even if its damage to just one blade). It is one of the disadvantages to blisks compared to regular rotors (where you can replace the individual blade).

It is also this cost and time that make blisks much less favourable to use currently in turbine section (where the tech is there to do so but maintenance needs are much higher) compared to compressor section where they have become almost universal now.

 

[Combat-Master]

 

[Afif]

https://twitter.com/i/web/status/1564552251410096135

is this mock up or prototype?

 

[Agha Sher]

is this mock up or prototype?

mock up

 

[Combat-Master]

Pretty amazing, TF6000 core can be used to make a turboshaft engine for ATAK-II/10-ton general purpose helicopter. Turboshaft engine could produce around 3500 to 4000 shp.

https://twitter.com/i/web/status/1564666796455624707

 

[Baris]

Pretty amazing, TF6000 core can be used to make a turboshaft engine for ATAK-II/10-ton general purpose helicopter. Turboshaft engine could produce around 3500 to 4000 shp.

https://twitter.com/i/web/status/1564666796455624707

"can" be used but probably not, just like the TS-1400 engine for T129 ATAK. We are slow when it comes to developing and adopting domestic engines.

 

[Brokengineer]

Pretty amazing, TF6000 core can be used to make a turboshaft engine for ATAK-II/10-ton general purpose helicopter. Turboshaft engine could produce around 3500 to 4000 shp.

https://twitter.com/i/web/status/1564666796455624707

Or increase the bpr to make a use for larger uavs.

 

[Maedhros]

Or increase the bpr to make a use for larger uavs.

Specifications of the engine of Global Hawk and TF-6000 are quite similar. Does anybody think TUSAS MIUS can be a HALE type surveillance and reconnaissance UAV?

 

[Combat-Master]

TS-1400 turboshaft engines for manned flights will be delivered to TAI by the end of the year

 

[Cabatli_TR]

TEI-TF6000 turbofan engine

• Design phase completed. Prototype production commenced
• First month of 2023, the production will be completed
• First quarter of 2023, First ignition of engine will be carried out
• We chosed the core of TF6000 for Atak-2. This core can generate 3500-4000lbs of power.
• Next step will be MMU engine

 

[Fighter_35]

TEI-TF6000 turbofan engine

• Design phase completed. Prototype production commenced
• First month of 2023, the production will be completed
• First quarter of 2023, First ignition of engine will be carried out
• We chosed the core of TF6000 for Atak-2. This core can generate 3500-4000lbs of power.
• Next step will be MMU engine

Hopefully tf6000 becomes successful and TFX engine will be designed right after. We really need engine technology

 

[Zafer]

First ignition of the TF6000 being in the first quarter of 2023 can mean that a usable UCAV engine can be obtained in just a year from today as I don't think they will take too much time optimizing it. If all goes well Kızılelma can even be flying with a TF6000 in its heart before 2023 ends. Of course this is probably the best case scenario. However I can not help but imagine Kızılelma flying with a TF6000 as early as mid 2023 in the real best case scenario. Should a pressing situation emerge this can very well happen.

 

[Radonsider]

Pretty amazing, TF6000 core can be used to make a turboshaft engine for ATAK-II/10-ton general purpose helicopter. Turboshaft engine could produce around 3500 to 4000 shp.

https://twitter.com/i/web/status/1564666796455624707

That's a lot of power!!