Chinese Engine Development

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latenlazy

Brigadier
taxiya said:
Rough translation of texts that you underlined (and not underlined but related)
First photo:
  1. XX15 engine inner and outer passage/duct matching optimization.
  2. XX20 engine fan blade vibration reduction.
  3. (not underlined) XX15 engine improvement batch full engine (not just core) dynamic (动力学) characteristic, abnormal (异常) load analysis and structure improvement/optimization according to the analysis.
  4. Intercooling gas turbine dynamic simulation and application.
  5. Axial symmetric TVC nuzzle A8 actuation system load distribution analysis.
  6. Research of key assembly technique and method of engine core of XX15 (improvement batch).
Second photo:
  1. A type of combustion chamber design.
  2. Design of inlet duct of 3rd batch XX15 based on MBD (massive diffusion bonding).
  3. Two stage high pressure turbine cooling blade of high thrust medium bypass ratio engine.
    1. Medium bypass engine. What is this? WS-10 and 15 are low bypass, WS-20 is high bypass.
    2. What does it mean by cooling blade (冷却叶片)? Should it be blade cooling (叶片冷却) instead?
  4. Research into the impact of surface material characteristic of an important engine type to stealthy coating.
It would be interesting to search for publications related to these awards, such as publications that the award receiver is one of the authors. From the publication we can tell when the work started. Then we know how long it has been etc.
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Sounds like the rumours of an iteration to the WS-15 already being in the works might have some validity to them.

Tirdent said:
Probably WS-20? If it's CFM56-ish (BPR 4-6) as rumoured it's what I'd nowadays describe as a medium bypass ratio engine - high bypass these days is >8 really (CJ-1000A, for example). With a two-stage HPT it's almost certainly not going to be the WS-15, which will probably adopt a single-stage HPT for weight and inertia reasons.

EDIT: actually, the two-stage HPT excludes the WS-20 too, doesn't it? The WS-10 core has a single-stage HPT as well. Hmm...
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My guess is the mid bypass engine could be for the H-20.

Maybe 冷却叶片 refers to “cooled blades” rather than “cooling blades”.

Edit: SDWatcher beat me to it.

Klon said:
According to some posters on cjdby, these are youth research projects (or something like that), so not necessarily actual cutting-edge work.
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Those sound like machine translations. Can you include the Chinese, or better yet the link? It’s worth perusing the comments on this one I think. Thanks.
 
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Tirdent

Junior Member
Registered Member
SDWatcher said:
高压= high pressure.
涡轮冷却= turbine cooled or intercooled turbine.
叶片= blade.

高压涡轮冷却叶片= blade of the high-pressure intercooled turbine or high-pressure intercooled turbine blade.

Intake air is cooled, not the blade.
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Or is the cooling air cooled? That would make sense for the NGVs (rotating blade cooling air has to pass through the hub, so no straightforward way of cooling it*), with a heat-exchanger in the bypass duct - the Russians are big fans of this approach (pioneered by the NK-144, other examples are the D-30F6 & AL-31F). The benefit is potentially huge, in an engine with a high OPR the HP compressor exit air (which has to be used for HPT cooling, as it's the only source of air at higher pressure than the HPT gas) is in fact anything but cool!

* It helps to have vanes which impart swirl to the cooling air before it enters the rotating parts though, as this reduces relative velocity (and thereby total temperature in the rotating frame of reference). I suppose that could actually be described as "cooling blades"?!

latenlazy said:
My guess is the mid bypass engine could be for the H-20.
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Possible - if true it would indicate that the engine is not a WS-10 derivative though, contrary to popular perception.
 
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SDWatcher

New Member
Registered Member
Tirdent said:
Or is the cooling air cooled?.......
I suppose that could actually be described as "cooling blades"?!
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涡轮冷却= turbine cooled or intercooled turbine.

Intake air is cooled, so that volume is reduced, while maintaining pressure before compression. As volume is reduced, work done by the compressor is also reduced, which in turn decreases input power for a fixed amount of air. It is standard procedure for an intercooled turbine.

It would be "unconventional", if you want to relate such cooling procedure to the blade.
 
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Tirdent

Junior Member
Registered Member
So "turbine" in this instance refers to the engine in its entirety (as in "gas turbine"), compressor and all, rather than just the turbine section? That wasn't clear from the translations provided to date.

If so, that's indeed pretty standard fare in terrestrial and naval applications (the MiG-25 is a rare example of an airborne turbine engine with [pre-compressor] cooling).
 
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SDWatcher

New Member
Registered Member
涡轮 is literally "turbine" in Chinese, which also means "gas turbine" or "turbine engine", when combined with 冷却, which is "cooled", would mean intercooled "gas turbine" or "turbine engine" within context.
 
mys_721tx

mys_721tx

Junior Member
Registered Member
SDWatcher said:
"大推力 中等涵道比 双级 高压涡轮冷却叶片 设计技术研究"

Research of design technology on high thrust, medium bypass ratio, dual stage, high-pressure intercooled turbine blade.
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"双级高压涡轮" is a proper term, two-stage high-pressure turbine, as in the one on LEAP.

It is the turbine blade being cooled.
 
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SDWatcher

New Member
Registered Member
In such a case, it should have been written as 叶片冷却, "blade cooling", instead of 冷却叶片, "cooled blade", referring to the other part of the sentence, of what is being 设计技术研究, "research of design technology".
 
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