It was a fireworks plant in the same vicinity as the engine company.
Chinese Engine Development
- Thread starter jackbh
- Start date
It was a fireworks plant in the same vicinity as the engine company.
But here it is mentioned there were two fires.
A screen capture of archival footage of Taihang on a test fixture.
Does anyone have the PLA requirement for WS-15? Then the dimensions and performance criteria maybe? also, the afterburner petals look shorter than what the CG videos about Taihang had shown.
Second fire was in the same industrial park as the engine plant but not in the engine plant itself. One of the guys from CJDBY asked his relative from the engine plant.
How is this post from two years ago relevant to news from these days?
We know that one WS-10 engine is called WS-10C. WS-10C is IPE?
Apparently Pupu just said that the next batch of J-20s will feature thrust enhanced Taihangs (the 14.5 tonne variant?) and that a new 16 tonne WS-10 variant was being developed. As for the designations, Pupu said the WS-10B had roughly 14 tonnes of thrust, not sure about the others.
As for the WS-15, the only news we got was that it entered flight tests on an aircraft that wasn't the J-20 (probably the J-11) back in April of last year. Haven't heard anything since ... hopefully no news means good news.
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Block I refers to the 4th generation single engine fighter's thrust requirement (170 kN to 180 kN) while Block H refers to the 4th generation double engine fighter's requirement (150 kN to 160 kN). Basically, these are the PLA's "requirements" for the WS-15, at least in terms of thrust rating. Note these are old design specifications from 2004 and the requirements may have gone up quite a bit given the large progress of the Chinese gas turbine industry.
Original Paper :
This is a rather interesting post I just found, originating in 2017. The author says the the WS-15 has a thrust between 17 and 18 tons based on a flow rate (流量) of roughly 137 kg/s and an unit flow rate (单位流量) of between 1.25 to 1.3 kgf/kgs typical of 4th generation aeroengines. Apparently, he extrapolated the 137 kg/s figure from this table published by the 624th Institute back in 2011, which he believes is in reference to data collected during the WS-15 core's high altitude testing. My Chinese is not good so if I left out any of the details, please do point out. Also, does anyone know how he got to the 137 kg/s figure from the table, since his description does not specify the calculation method.
H represents altitude 0, M represents speed 0, Ga represents intake air flow, state (状态) represents 100% speed, and T1 represents afterburner temperature.
His accompanying description in Chinese for reference : 表格中只要看最下面一行就行了，H代表高度0，M代表速度0，Ga表示进气流量，状态代表100%的转速，T1代表加力温度。上面那篇论文的时间是2011年，作者是燃气涡轮院的，当时WS15正处于验证机研制的阶段，因此相应的数据也就是在处于研制阶段的WS15验证机在高空台上的试验点。验证机阶段国内是按照原型机96%的指标来研制，也就是说在验证机阶段只需要达到原型机96%的性能指标就行了，因此也就是说原型机的推力一般比验证机达到的推力大5%。按照表格上130Kg/S流量的数据，WS15原型机的流量约为137Kg/S流量的级别，按照四代机单位流量推力为1.25到1.3Kgf/KgS的水平，那么推算出WS15的推力范围为17吨到18吨附近，比产品30稍大，两者的推力差别大概为1到2吨，军推推力为11吨到12吨之间。
H represents altitude 0, M represents speed 0, Ga represents intake air flow, state (状态) represents 100% speed, and T1 represents afterburner temperature.
His accompanying description in Chinese for reference : 表格中只要看最下面一行就行了，H代表高度0，M代表速度0，Ga表示进气流量，状态代表100%的转速，T1代表加力温度。上面那篇论文的时间是2011年，作者是燃气涡轮院的，当时WS15正处于验证机研制的阶段，因此相应的数据也就是在处于研制阶段的WS15验证机在高空台上的试验点。验证机阶段国内是按照原型机96%的指标来研制，也就是说在验证机阶段只需要达到原型机96%的性能指标就行了，因此也就是说原型机的推力一般比验证机达到的推力大5%。按照表格上130Kg/S流量的数据，WS15原型机的流量约为137Kg/S流量的级别，按照四代机单位流量推力为1.25到1.3Kgf/KgS的水平，那么推算出WS15的推力范围为17吨到18吨附近，比产品30稍大，两者的推力差别大概为1到2吨，军推推力为11吨到12吨之间。
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He believes WS-15 specifications given in a 2011 article reflected the test state which according to standards at the time was set at 96% of final intended parameters. He then divided the 130kg/s test state mass flow rate by 0.96 to get 137kg/s for the final engine state.
1.25-1.3kgf/kgs is supposed to be the specific thrust but he got the scale wrong and is off by two magnitudes, it should actually be 125-130kgf/kgs. Net thrust can then be calculated by 137kg/s x 125kgf/kgs = ~17t force. All in all, his logic is sound and the specific thrust assumption appears reasonable considering its two biggest determinants, TIT and bypass ratio, are both parameters that AVIC was confirmed to have changed from WS-10 to WS-15 to achieve higher specific thrust. The question remains how successful AVIC was in its effort to increase TIT and whether the 137kg/s mass flow rate inferred from a 2011 article is reflective of the final WS-15.