Chinese Engine Development

L

latenlazy

Brigadier
sequ said:
This seems to be on par with the EJ200.

And how come their engines are so much lighter than western equivalents? Don't they include the weight of the gearbox and and fluids?
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EJ200 is a medium weight class engine, not a large weight class engine.

Izd 30 has a 5 stage HP compressor instead of a 6 stage HP compressor so one fewer stages probably contributes to the lower weight.

(I know Deino already put a cap on this conversation but I do think the general knowledge is useful for general audience comprehension of these topics).
 
by78

by78

General
An undated image showing two small turbojets (95kg and 190kg, respectively) undergoing testing on a high-altitude plateau (presumably Tibet). I wonder what the engines are.

53033059143_1e4020f6ee_h.jpg
 
R

Red tsunami

Junior Member
Registered Member
RadDisconnect said:
Another point of comparison is some data about the izd.30 that was released by Saturn and posted on Secret Projects and another link about the engine for the Sukhoi LTS.

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So looking at the charts and the translated report, the izd.30 seems like a good engine, but not what the "Russia strong" crowd keeps hyping it up to be. So the izd.30 has 19% better T/W than the AL-41F1, which has a weight of about 1,600 kg and thrust of 14.5 metric tons or 32,000 lbs (15 metric tons or 33,000 lbs in emergency mode), which means T/W of 9.06. This means that izd.30 has T/W of 10.8, so when combined with estimated weight of 1,500 kg, that means 16.2 metric tons or 35,700 lbs full afterburner and 16.7 metric tons or 36,800 lbs in emergency mode. Similarly, the link said that engine of the 5th generation, which likely refers to izd.30, has 30% more thrust than AL-31FP which has 12.5 metric tons of thrust, so this would result in 16.25 metric tons or 35,800 lbs of thrust for izd.30. Which is decent but not amazing considering it's more than 20 years newer than F119.

The specific thrust of AL-41F1 being only 6% lower than izd.30 also doesn't make the izd.30 seem that impressive. Since it fits in the same footprint as the AL-41F1, it's unlikely to have more than 10% higher air flow, which means that it only produces 17% more dry thrust, and considering that Su-57 with AL-41F1 only supercruise at Mach 1.3 or 1.4, some fantastical claims about Su-57's supercruise at Mach 2 with izd.30 is also very unlikely. However, it likely will allow Mach 1.5-1.6 supercruise which is respectable.

The durability of 6,000 hours for the izd.30 is also an improvement over the AL-41F1 with 1,000 hours TBO and 4,000 hours total life, but that's still short of the F119, which has 2,000 hours TBO for hot section, 4,000 hours for cold section, and 8,000 hours life.
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I would like to remind you that the engine T/W and other data have Russian standards, American standards, French standards, and Chinese standards. For example, the rules they follow when calculating engine weight are likely to be different.
 
L

latenlazy

Brigadier
siegecrossbow said:
Look what I found...
View attachment 115794

View attachment 115793
Supposedly YWH-30-27 is the initial requirement for WS-15's core.
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Yeah but we had this table and the full document it’s from years ago haha. It’s buried somewhere in earlier days of this thread.

Also note the engine listed above it. That should be the WS-10 and they exceeded its original thrust range.
 
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