Can you elaborate on what the expectation of "superior technology to F135" means?
For what it's worth, my expectation has always been a F414, EJ200 class engine.
Chinese Engine Development
- Thread starter jackbh
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Can you elaborate on what the expectation of "superior technology to F135" means?
For what it's worth, my expectation has always been a F414, EJ200 class engine.
Rough translation
Performance parameters of a certain advanced medium-thrust engine: Maximum sea-level takeoff thrust: 10-11 tons Turbine inlet temperature: 1950-2100K Image source: See watermark
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Really encouraging turbine inlet temp.
Edit: Reading a bit more, I'm going to be a bit cautious and assume that this is just a preliminary list of requirements/goals rather than something currently being tested.
More (related) information on said engine, posted by @Rational314159 on Twitter:
Intermediate thrust: 70kN
Afterburning thrust: 110kN
3-5-1-1 Configuration
Bypass ratio: 0.5
Intermediate fuel consumption: 0.8kg/daN/hr
Afterburning fuel consumption: 1.6kg/daN/hr
People were hyping it up to be a super EJ270 with the most cutting edge technology comparable to WS-15(Which is supposedly the best engine until next gen VCE comes out).
I think your expectations were far too high, what about a TIT of 2100K is not impressive to you?
F-135 is at 2260K and is decade old technology
Engine specs are not like Dragonball Z power levels. For example, if you can extract more work out of a lower TIT that lower TIT would actually indicate more advanced capabilities, not less.
Alfa was hyping F-414EPE/EJ-270 stats. Compared to that, these numbers are decidedly middling.
Rough translation
Performance parameters of a certain advanced medium-thrust engine: Maximum sea-level takeoff thrust: 10-11 tons Turbine inlet temperature: 1950-2100K Image source: See watermark
____
Really encouraging turbine inlet temp.
Edit: Reading a bit more, I'm going to be a bit cautious and assume that this is just a preliminary list of requirements/goals rather than something currently being tested.
I'm not familiar with these people on Twitter, or the validity of their sources.
Is there any reason to believe these are anything more than just idle speculation from random people on the internet?
F-414EPE and EJ-270 never actually got built and the WS-19 is only just entering service (if the chatter around it is true). There will be future improvements. Not much to gripe about here.
so says here that for afterburner, the maximum outlet chamber temperature is 2050K. Which seems to be pretty high? Would make this a 5th gen engine. I'm not translating this correctly but it seems like temperature here is outlet instead of inlet temperature? You need pretty advanced materials to handle that.
Also keep in mind that for RD-33, its dry thrust is 50kN and wet thrust is 81kN. And that is measured in cold Russian environment while WS-19 would have to reach certainly level in much hotter and humid China (especially around SCS, where CV-18 will have to operate).
So, getting to 70kN and 110kN is a pretty big jump for something similar in size (that's 40% greater dry thrust and 36% higher wet thrust). Even if engine is slightly heavier, it would still be a TWR of 10 level of engine. That seems pretty solid to me.
Is there something I'm not getting here? This seems to be beyond what I would expect for WS-19.
What are people still complaining about?