TR Propulsion Systems

[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.