TR Propulsion Systems

[Bilge adam reis]

400 yes, and now search up how many accidents happened and how many people died during those tests...

Only a small batch of ~20 Gökbeys were ordered so far, first delivered end of September 2024, the branches of the military will also test them, the engines and helicopter are currently forcold climate tests in Sweden.

You're either for trolling here or you really are a joke like that guy on your pp.

Lots of F16s crashed too does that make them bad planes?

Also these tests are just for the civilian one, think about how many years the militarized one wll take.

 

[CAN_TR]

Lots of F16s crashed too does that make them bad planes?

Also these tests are just for the civilian one, think about how many years the militarized one wll take.

30 people involved in the V22 project died during the development phase, so what i'm saying is rather slow and steady that fast and half assed which could result in fatal accidents.

 

[TheInsider]

Red is thrust; green is RPM. Even though this is not a mature engine, it looks good. I expect the TF-6000 to max at 25k RPM. According to a simple calculation, the TF-6000 will generate 6800N @ 25k RPM.

TS-1400 showed good gains in the maturing process. Let's see how it will go this time for the TF-6000.

 

[hugh]

View attachment 74205

Red is thrust; green is RPM. Even though this is not a mature engine, it looks good. I expect the TF-6000 to max at 25k RPM. According to a simple calculation, the TF-6000 will generate 6800N @ 25k RPM.

TS-1400 showed good gains in the maturing process. Let's see how it will go this time for the TF-6000.

Only 6800N? It should produce around 27k N thrust if 6000lbf is achieved.

Question: why is there two different RPMs, namely N1 and N2?

 

[TheInsider]

Only 6800N? It should produce around 27k N thrust if 6000lbf is achieved.

Question: why is there two different RPMs, namely N1 and N2?

You are right. I was too preoccupied with the current situation(reading news about the Imamoğlu protests), and I confused newton with lbf.

 

[hugh]

Maximum sustained thrust should have been announced by now. Or more test videos. Something more than this.

Based on the displayed net thrust of 15,181 N (approximately 3,413 lbf), the possible maximum thrust of this engine could be in the range of 5,000 to 7,000 lbf, assuming the test was not conducted at full throttle.

15,181 is an rpm value, not thrust. A quick googling taught me that N1 is fan speed and N2 is the speed at engine core(it's a two-spool engine). Though, I don't know enough about turbofans to make sense of these figures. My guess is that engine speed and thrust do not progress linearly, otherwise, 4k N thrust is abysmal

 

[DBdev]

• N1 = 6,451 RPM and N2 = 15,181 RPM, the engine produces 921 lbf, which is only 15.35% of the 6,000 lbf target.
• This suggests the engine is either operating at a very low power setting (e.g., partial throttle) or is significantly under performing.
• N2 = 38,704 RPM could achieve 6000lbf if everything else is right.
  
  This is also within the realm of possibility for a high-pressure spool. High-performance jet engines can have N2 speeds exceeding 30,000 RPM, especially in smaller engines where the high-pressure components are compact and designed to spin faster.
  
  14967 was the highest RPM they showed at first video more than a year ago but at that RPM thrust seemed a lot more than 921lbf they are getting at 15181 RPM from this new test. I am confused.
  
  @Nilgiri what do you think should we worry about long silence and these low thrust numbers?

 

[Nilgiri]

Only 6800N? It should produce around 27k N thrust if 6000lbf is achieved.

Question: why is there two different RPMs, namely N1 and N2?

15,181 is an rpm value, not thrust. A quick googling taught me that N1 is fan speed and N2 is the speed at engine core(it's a two-spool engine). Though, I don't know enough about turbofans to make sense of these figures. My guess is that engine speed and thrust do not progress linearly, otherwise, 4k N thrust is abysmal

• N1 = 6,451 RPM and N2 = 15,181 RPM, the engine produces 921 lbf, which is only 15.35% of the 6,000 lbf target.
• This suggests the engine is either operating at a very low power setting (e.g., partial throttle) or is significantly under performing.
• N2 = 38,704 RPM could achieve 6000lbf if everything else is right.
  
  This is also within the realm of possibility for a high-pressure spool. High-performance jet engines can have N2 speeds exceeding 30,000 RPM, especially in smaller engines where the high-pressure components are compact and designed to spin faster.
  
  14967 was the highest RPM they showed at first video more than a year ago but at that RPM thrust seemed a lot more than 921lbf they are getting at 15181 RPM from this new test. I am confused.
  
  @Nilgiri what do you think should we worry about long silence and these low thrust numbers?

Generally turbofans of this size/class (say 5k lbf - 10k lbf max thrust).. have the HP core (N2) run in the 40k+ RPM range at peak thrust.

N1 (to LP spool + Fan, given Fan's larger diameter) that just depends on the N2 as it happens consequentially.

So we don't know if there is a further ramp up from the 15k (and the thrust this produces) when this picture was taken.

If there is test video, maybe there is more information there.

Understandable if they keeping it close to chest in testing phase of engine though.

 

[TheInsider]

• N1 = 6,451 RPM and N2 = 15,181 RPM, the engine produces 921 lbf, which is only 15.35% of the 6,000 lbf target.
• This suggests the engine is either operating at a very low power setting (e.g., partial throttle) or is significantly under performing.
• N2 = 38,704 RPM could achieve 6000lbf if everything else is right.
  
  This is also within the realm of possibility for a high-pressure spool. High-performance jet engines can have N2 speeds exceeding 30,000 RPM, especially in smaller engines where the high-pressure components are compact and designed to spin faster.
  
  14967 was the highest RPM they showed at first video more than a year ago but at that RPM thrust seemed a lot more than 921lbf they are getting at 15181 RPM from this new test. I am confused.
  
  @Nilgiri what do you think should we worry about long silence and these low thrust numbers?

I asked around, and this picture was taken after the engine stopped and while it was slowing down. In this picture, there is no combustion inside the combustion chamber. It takes a while for fans and turbines to completely stop and a small amount of thrust is produced.

 

[TheInsider]

https://twitter.com/i/web/status/1907898788372688921

Interesting... Baykar bought furnaces required for the casting/production of directionally solidified(dx) and single-crystal (sx) turbine blades.

My guess is they will start with production of dx turbine blades from Ukranian origin but i don't rule out a possible single-crystal move as the developer of Turkish single-crystal turbine blades Assoc Prof. Dr. Havva Kazdal Zeytin is working as an advisor to Baykar.

Baykar will be the second company after TEI, to be able to produce dx/sx turbine blades.

Of course, things don't end there as Baykar will need its own recipes for many processes like forging superalloy, titanium forging, cooling canal designs of turbine blades, thermal coatings/barriers etc.

 

[Oublious]

Baykar is going to pimp Ukraine engine up,tuning ekspertize Baykar...

 

[hugh]

Baykar is going to pimp Ukraine engine up,tuning ekspertize Baykar...

English please

 

[uçuyorum]

https://twitter.com/i/web/status/1907898788372688921

Interesting... Baykar bought furnaces required for the casting/production of directionally solidified(dx) and single-crystal (sx) turbine blades.

My guess is they will start with production of dx turbine blades from Ukranian origin but i don't rule out a possible single-crystal move as the developer of Turkish single-crystal turbine blades Assoc Prof. Dr. Havva Kazdal Zeytin is working as an advisor to Baykar.

Baykar will be the second company after TEI, to be able to produce dx/sx turbine blades.

Of course, things don't end there as Baykar will need its own recipes for many processes like forging superalloy, titanium forging, cooling canal designs of turbine blades, thermal coatings/barriers etc.

I had heard they have a top team of metallurgists working on developing single crystal solutions for a while

 

[Agha Sher]

Baykar is going to pimp Ukraine engine up,tuning ekspertize Baykar...

What kind of % performance improvements would be realistic, if they upgrade AI-322F/TF with single crystal tech?

@TheInsider

 

[Oublious]

Congrats to Kale...

https://twitter.com/i/web/status/1908193269780996267

 

[Lool]

Congrats to Kale...

https://twitter.com/i/web/status/1908193269780996267

Congrats to KALE and Turkey for the major achievement
yet, still cant comprehend how on Earth did KALE manage to sell their engines before TEI
Iam sure that TEI did have some really good engines in certain classes; surely some countries may be interested in that, right?

 

[fushkee]

TEI and Kale, in fact did a kind of work sharing on producing jet engines. For missiles, Kale will produce and for aircrafts, TEI will produce. TEI made a TJ300 For only technology demonstration but never focused on those kind of small diameter jet engines. That’s why Kale entered the market for small diameter jet engines and TEI is focusing S/IHA and KAAN engines.

 

[Huelague]

TEI and Kale, in fact did a kind of work sharing on producing jet engines. For missiles, Kale will produce and for aircrafts, TEI will produce. TEI made a TJ300 For only technology demonstration but never focused on those kind of small diameter jet engines. That’s why Kale entered the market for small diameter jet engines and TEI is focusing S/IHA and KAAN engines.

TEI = reusable engines, Kale = disposable engines

 

[Shtr]

Kale is working on reusable engines too

 

[Oublious]

Bayraktar TB2 Test Flight with
Baykar-Made “TM100” Engine

What is happening? When did they make ther own engine? It is a good thing i am happy but i am surprised tooo