Perhaps only the ones on the right side (3rd stage) of this diagram will make work of you.
Chinese Engine Development
- Thread starter jackbh
- Start date
Perhaps only the ones on the right side (3rd stage) of this diagram will make work of you.
True, true. Just some documentary confirmations at this point.
Was initially kinda hopeful that the WS-19 can actually reach the level of F414-EPE, but that's going to be naively asking for too much.
So for now, 10 tons (or 98.1 kN) is likely the best answer that us outsiders can have.
But perhaps, future advanced iterations can allow the WS-19 to reach such goals.
Last edited:
WS-19 base variant maximum thrust will be 10+ tons as per the chief designer. rest we don't know much..
WS-19 borrowed components/materials from WS-15 so service life, TBO and other specifications will be good as WS-15 engine. and the most important thing, development cycle is the shortest one in China's aero engine history. will be the benchmark for incoming projects.
Guizhou(GAIC) have implemented digitalization and advance manufacturing process. which reduced 25 percent development time of WS-19 engine.
------------------------------------------------------------------------------------------------------------------------
in April this year, GAIC held a ceremony to mark the concentrated commencement and operation of 22 aviation engine related projects with a total investment of 5.2 billion yuan..
Among these projects, 14 new projects worth 4.6 billion yuan have already begun construction, while another eight projects with a combined investment of 600 million yuan have been put into operation.
------------------------------------------------------------------------------------------------------------------
from first flight to material selection and new facilities construction, WS-19 serial production is not far away..
Actually, didn't someone pitched out a figure of 13,000 kgf (~127.5 kN) here for the production model? That's is way above F414-EPE's 117 kN and even higher than early AL-31 variants.
I'm under the impression that 98.1 kN is the *minimum* figure for WS-19, and the WS-21 already has a thrust similar to that (although I'd assume with worse thrust curves).
Yup. That's what I heard too. IIRC it's the demonstrator that achieved the 10+ tonnes-force/98 kN figure, and the actual production variant will be more powerful.
So similarities and parallels with WS-15, but WS-19 isn't exactly based on the WS-15. It's *not* a smaller WS-15, is that right?
It's nice to see WS-19 after all the hiccups in the WS-10/15 programs.
But is the program moving so fast that it'll be in service with the J-35 from the get-go?
And would it get 2D TVC?
I have a couple thoughts on that.
When we compare the WS-19 to other engines, we tend to just compare the maximum thrust figures. Same thing here. When we say "the WS-19 is expected to be comparable with the F414-EPE," most of the time we mean thrust (I usually will specify), not thrust curves.
The thing is, we have no clear idea about the WS-19's thrust curves. However, given:
- F414 does have quite questionable supersonic performance (inherited from the F404 IIRC). It's equipped on the Rhinos (aka F/A-18s) which already is a very draggy airframe.
- The F-35 family, which is (I think?) the J-35's direct competitor, having also questionable supersonic performance (max speed M1.6)
The J-35 is almost certain to be designed with those factors in mind to exploit them. And, we know the J-35 shares similarities in some components with the WS-15, which is supersonically oriented.
So, there's a high chance the WS-19 will be for supersonic speeds. Plus, it's a medium bypass engine. It's asier to have a smaller bypass ratio in a medium bypass engine.
Last edited:
I've seen some claims regarding the core mass flow rate of the WS-15 being around 35kg/s.
Though, claims on the Internet says that the F119 has an overall mass flow rate of 77 kg.
How come? The overall mass flow rate of F119 is somehow more than two times the core mass flow rate of the WS-15, when they have a similar BPR.
Which one of these claims are bull or did I miss a unit somewhere? Do we have any remote idea about the overall/core mass flow rate and pressure ratio about the WS-15 (even WS-19) at all?
Though, claims on the Internet says that the F119 has an overall mass flow rate of 77 kg.
How come? The overall mass flow rate of F119 is somehow more than two times the core mass flow rate of the WS-15, when they have a similar BPR.
Which one of these claims are bull or did I miss a unit somewhere? Do we have any remote idea about the overall/core mass flow rate and pressure ratio about the WS-15 (even WS-19) at all?
Uh. Core mass flow is only the HPC section. Total mass flow includes LPC and fan.
two different projects undertaking by two different institutes.. WS-19 is a new design and not based on WS-15.. but the supply chain is interconnected.
GAIS invested 5.2 billion RMB in 22 aviation engine related projects just to expand the facilities across all domains from components manufacturing to testing to R&D.