no, I'm still thinking about how credible Galleon tables are...
WS-15 -> 180 kN -> SF-A(??) core - > 13 t
WS-10A -> 132 kN -> WS118 core -> 12 t
something very wrong here
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Chinese Engine Development
- Thread starter jackbh
- Start date
WS-15 -> 180 kN -> SF-A(??) core - > 13 t
WS-10A -> 132 kN -> WS118 core -> 12 t
something very wrong here
Maybe they went with efficiency over power?
Since those are develop for civilian programme. The demand for low noise level reduction might affect the level of performance.
AssassinsMace
Lieutenant General
The thrust given for WS-15 and WS-10A are those with A/B. Dry thrust is lower than thrust with A/B and lower than the thrust of a high by-pass ratio engine with the same engine core.
Quickie
Colonel
My understanding is the higher the bypass, the lesser the thrust. The plus point is the fuel efficiency increases in return for the reduced max thrust.
At lower speed the higher the by-pass ratio the higher the thrust.
AeroEngineer
Junior Member
SF-A will have a lot more thrust than 13 tons for sure, it uses WS-15 core so basically it will be on par witht the American PW-F-117 with about 18 tons of turst, remember SF-A will have a very large by pass ratio of 6, so even without after burner it will have the same amount of thrusts due to the high by pass ratio.
As for WS-118, we know that WS-10A has 8 tons of thrust without using after burner, so the 13 tons thrust for WS-118 seems to be right with a by pass ratio of 5.5. The main improvement of the WS-118 is that it is 20% more fuel efficient than the D-30 thus giving Y-20 much higher load capacity.
Y-20 flying with D-30 has only 55 tons of max load, still better than the IL-76MD but less than te IL-476. Y-20 with WS-118 however, will be better than both IL-76MD and IL-476, due to its much larger cargo area.
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