本文選題：雷諾數(shù) + 高旋轉(zhuǎn)數(shù)��； 參考：《航空動(dòng)力學(xué)報(bào)》2016年02期

【摘要】：為匹配真實(shí)發(fā)動(dòng)機(jī)轉(zhuǎn)子葉片的工作條件,將實(shí)驗(yàn)回轉(zhuǎn)通道氣體壓力提高到500kPa以上,使雷諾數(shù)和旋轉(zhuǎn)數(shù)范圍分別擴(kuò)展到10 000~70 000和0~2.08.在此基礎(chǔ)上通過實(shí)驗(yàn)方法研究了高旋轉(zhuǎn)數(shù)下帶45°傾角斜肋的方形截面回轉(zhuǎn)通道的換熱特性.結(jié)果表明:回轉(zhuǎn)通道的第1通道前緣面?zhèn)鳠嵯禂?shù)隨旋轉(zhuǎn)數(shù)的增大先減小,在達(dá)到臨界旋轉(zhuǎn)數(shù)后換熱隨旋轉(zhuǎn)數(shù)增大而增強(qiáng);低旋轉(zhuǎn)數(shù)下,回轉(zhuǎn)通道的第2通道前后緣面換熱差異較小,隨著旋轉(zhuǎn)數(shù)的增大,前緣面換熱始終強(qiáng)于后緣面,這種換熱特性與光滑通道完全不同.
[Abstract]:In order to match the operating conditions of the real engine rotor blade, the gas pressure of the experimental rotary channel is increased to above 500kPa, and the range of Reynolds number and rotation number is extended to 10 000 t 70000 and 0 0 0 2. 08 respectively. On the basis of this, the heat transfer characteristics of a square cross-section rotary channel with 45 擄inclined rib at high rotation number are studied by experimental method. The results show that the heat transfer coefficient of the front surface of the first channel decreases first with the increase of the number of rotations, and increases with the increase of the number of rotations when the critical number of rotation is reached, and the heat transfer increases with the increase of the number of rotations at low rotation number. The difference of heat transfer between the front and back sides of the second channel is small. With the increase of the rotation number, the heat transfer of the front edge is always stronger than that of the rear edge, which is completely different from that of the smooth channel.
【作者單位】： 中國航空工業(yè)集團(tuán)公司中航商用航空發(fā)動(dòng)機(jī)有限責(zé)任公司設(shè)計(jì)研發(fā)中心;北京航空航天大學(xué)能源與動(dòng)力工程學(xué)院航空發(fā)動(dòng)機(jī)氣動(dòng)熱力國家級(jí)重點(diǎn)實(shí)驗(yàn)室;
【分類號(hào)】：V231.1

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