Chinese Engine Development

[Alfa_Particle]

WS-19?

Allegedly. The high TWR and thrust range strongly points towards the WS-19.

 

[CaribouTruth]

- High TWR
- Max static takeoff thrust: 10-11,000 kgf
- T4: 1950-2100 K
- 15-20%/30% decrease in fuel consumption compared to last-gen engines in the same class (TWR 8, WS-21?)
- 20%/50% improvement in reliability
- cost improvements

Jeez. Two of these would absolutely wreck an F135.

IF this really represents the WS-19 (or any other operational engine for that matter), the specific thrust value of 120-130daN/(kg/s) would be inline with the cutting edge engines around, iirc F119 has 140daN/(kg/s) on the high end, F135 - 125-135daN/(kg/s), EJ200 - 125daN/(kg/s).

 

[broadsword]

- High TWR

What's the number?

 

[Alfa_Particle]

What's the number?

Unspecified. >>8?

 

[broadsword]

Unspecified. >>8?

Dry?

 

[sutton999]

It is comparing Turbofan A and Turbofan B to Turbofan old T/W=8 (say RD93/WS13).
So, two advanced Turbofan A ( let's say WS21) and Turbofan B( let's say WS19).

 

[sunnymaxi]

Dry?

its for older variants most likely for WS-13E.. which is ''8''

 

[Alfa_Particle]

Dry?

Wet. >>8 means much higher than 8.

It is comparing Turbofan A and Turbofan B to Turbofan old T/W=8 (say RD93/WS13).
So, two advanced Turbofan A ( let's say WS21) and Turbofan B( let's say WS19).

I'm thinking two-stages instead of two entirely different engines.

 

[Tomboy]

If this is WS-19 than it is very underwelming compared to what we were expecting, isn't the expected thrust up to 127kN and superior technology to F-135?

 

[MeiouHades]

If this is WS-19 than it is very underwelming compared to what we were expecting, isn't the expected thrust up to 127kN and superior technology to F-135?

That may just be its theoretical maximum, that doesn't mean that's what it'll be run at.