J-20 5th Gen Fighter Thread VI
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It's from Zhuhai Airshow 2016, taken during the J-20's public debut.
What he said was that WS-15 was planned for mass production after 2020 and that the WS-10 was supposed to equip the first batch of J-20s in the very beginning. However, progress delays on the WS-10 led to the current situation with AL-31s.
Are you sure it's "after 2020"? There's another comment following that and from the context by 2020 seems to make more sense than after 2020.
2020后 means after or following 2020.
He's been saying that for a while. The original 2020 delivery date was the goal originally set by 624th before the project got transferred to 606th. The latter affirmed their intentions to abide by the original schedule but gongke is sceptical on their ability to do so given their performance on the WS-10.
However, 606th is the only institute in China that has ever brought a high-thrust engine to fruition so it's easy to see AVIC's logic in transferring the WS-15 project to them. 624th, meanwhile, undertook low-thrust and medium-thrust projects that have gone much more smoothly than the WS-10 but lower-thrust projects are inherently easier than high-thrust projects.
While we're on the subject of the WS-15, has the information in this 2011 article been confirmed or refuted in the meantime?
Quite a lot of detail on the engine architecture (3F+6C+1LPT+1HPT) and technology (VIGVs on the fan, 2 stages with VSVs in the HPC, blisks in the second and third fan stages, composite bypass duct shell, radial afterburner flame holders, powder metallurgy discs, brush seals...).
At the time, the specs were apparently:
Reheated thrust:--------------161.865 kN
Dry trust:------------------------105.22 kN
Reheated TSFC:-------------2.02 kg/(kgf*h)
Dry TSFC:----------------------0.665 kg/(kgf*h)
Thrust/Weight ratio?:--------8.86
Air mass flow:-----------------138 kg/s
Bypass ratio:------------------0.382
Overall pressure ratio:------28.71
Turbine inlet temperature:--1477°C (= 1750 K)
Inlet diameter:-----------------1.02 m?
Length:--------------------------5.05 m?
Dry weight:---------------------1862.3 kg
Kind of an F141 EDE on steroids - has anything new come to light since then?
Quite a lot of detail on the engine architecture (3F+6C+1LPT+1HPT) and technology (VIGVs on the fan, 2 stages with VSVs in the HPC, blisks in the second and third fan stages, composite bypass duct shell, radial afterburner flame holders, powder metallurgy discs, brush seals...).
At the time, the specs were apparently:
Reheated thrust:--------------161.865 kN
Dry trust:------------------------105.22 kN
Reheated TSFC:-------------2.02 kg/(kgf*h)
Dry TSFC:----------------------0.665 kg/(kgf*h)
Thrust/Weight ratio?:--------8.86
Air mass flow:-----------------138 kg/s
Bypass ratio:------------------0.382
Overall pressure ratio:------28.71
Turbine inlet temperature:--1477°C (= 1750 K)
Inlet diameter:-----------------1.02 m?
Length:--------------------------5.05 m?
Dry weight:---------------------1862.3 kg
Kind of an F141 EDE on steroids - has anything new come to light since then?
These statistics have been re-posted for years and have proven to be inaccurate. When you get such precise figures, you can count on them to be false. Anyway, here are the parameters for the YWH-30-27/CJ-2000 (WS-15 core) written by lead designer Jiang Hefu (624). It's pretty old, but it gives you a good idea of what the WS-15 will look like.
Credits to vicent, mountaineer, sinosoldier, and latenlazy for the info over on CDF
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SinoSoldier
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Thanks for the credit, but I don't think I ever posted these LOL
Thanks!
There are a lot of significant digits, but nothing that would immediately mark them as false (other than dry sfc being rather optimistic perhaps). OTOH, what does the mass flow in kg/s refer to in the specs you posted - seems way too low for total engine mass flow and still far too low for core mass flow? Bypass mass flow (but you say it's the core) would be possible I suppose? Is there any info on the architecture (stage counts, essentially)?
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