ChineseTiger1986
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Well, this J-10B is not the prototype 1035, so maybe all the coming J-10B will depend on the WS-10A engine.
The WS-10A for J-10B in the mass production
- Thread starter ChineseTiger1986
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The very first J-10 become operational, it will debut.
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What problem stops WS10A fit on J10 in service util now? the production volume or other technique issue?
Recent article has said that WS-10 for J-10 has passed plateau experiment, so it will be soon.
Production issue. The crystal blade requirement is indeed difficult to meet but China production level has improvement and all the planes from J-11BS, J-15, and J-10B with WS-10A will debut next year for operation.
In fact, if you follow recent PLAAF, all new J-11B enter service are equipped with WS-10AM and no more AL-31 engine.
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what is the difference between WS10A and WS10AM?
will J10b fit WS15 in the future?
Acutually J10 is more cool fit WS10 than AL31, it looks more killer.
Does our country have the ability to produce crystal blade right now?
What is the MAX thrust power of the newest WS10 variant?
Will WS10 be modified to have thrust vectoring ability ? How many WS10 engine that China could produce per year?
although many years past, WS10 engine is still very myusterious for me.
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Sorry, its typo mistake. There is no WS-10AM .
No
Yes
WS-10A believes to be in 132kn thrust range
No, 200 -300 engines per year shall be fine
I might be wrong, but I think they are able to produce 2nd and up to 3rd generation blades.
From the patent below, it appears they may currently be working on 4th gen blades.
"Fourth-generation single-crystal high temperature alloy with high strength and stable structure and preparation method thereof
CN 103382536 A
Abstract
The invention relates to the field of high-strength single-crystal high temperature alloys and especially provides a fourth-generation single-crystal high temperature alloy with high strength and a stable structure and a preparation method thereof. The alloy is mainly applicable to aero-engine blade materials used at a temperature higher than 1100 DEG C. Chemical components of the alloy comprise, by weight, 3 to 5% of Cr, 5 to 12% of Co, 6 to 8% of W, 0.1 to 2% of Mo, 4.5 to 6% of Re, 2 to 4% of Ru, 5.5 to 6.5% of Al and 6 to 10% of Ta, with the balance being Ni. The preparation method comprises the following steps: preparing a single-crystal blade or test rod under the conditions that temperature gradient of a single crystal growth furnace is in a range of 40 K/cm to 80 K/cm, casting temperature is 1480 to 1550 DEG C, shuttering temperature is consistent with the casting temperature and a growth rate is 4 to 8 mm/min; and then carrying out solid solution homogenization treatment, high temperature aging treatment and low temperature aging treatment so as to allow the alloy provided by the invention to have high endurance strength. The alloy has a life of no less than 100 h in endurance conditions of a temperature of 1140 DEG C and a pressure of 137 MPa and has endurance strength equivalent to the endurance strength of an EPM102 alloy; and the alloy has the advantages of good structure stability at a high temperature, a wide heat treatment window and easily controllable solid solution treatment."
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