高旋转数下直肋U型方通道的换热特性研究

发布时间：2018-01-17 20:03

本文关键词：高旋转数下直肋U型方通道的换热特性研究　出处：《推进技术》2016年03期 　论文类型：期刊论文

【摘要】：通过提高U型通道气体压力到500k Pa以上,将实验雷诺数Re和旋转数Ro范围分别扩展到10000~70000和0~2.0,从而匹配真实发动机转子叶片的工作条件。在此基础上实验研究了高旋转数下带直肋的、方形截面的U型通道的换热特性。研究结果表明:第一通道前缘面的努塞尔数比随旋转数的增大先下降后增强,该临界旋转数为定值Roc=0.26;随着旋转数的增大,第二通道前缘面的努塞尔数比一直高于后缘面,与光滑通道中的换热规律不同;随着旋转数的增大,第二通道内外侧面努塞尔数比的差异逐渐减小,在临近出口处几乎没有差异,与光滑通道相比正好相反。
[Abstract]:By increasing the gas pressure of U-channel to more than 500kPa, the range of Reynolds number re and rotation number R _ o is extended to 10000g / 70000 and 0U 2.0, respectively. Thus matching the working conditions of real engine rotor blades, the straight ribbed rotor blades with high rotation number are experimentally studied. The results show that the Nussel number of the front surface of the first channel decreases first and then increases with the increase of the rotation number, and the critical rotation number is constant Rocan 0.26; With the increase of rotation number, the Nussel number ratio of the front surface of the second channel is always higher than that of the rear edge surface, which is different from the heat transfer law in the smooth channel. With the increase of rotation number, the difference of Nussell-number ratio between inside and outside of the second channel decreases gradually, and there is almost no difference near the exit, which is opposite to the smooth channel.
【作者单位】：中航商用航空发动机有限责任公司设计研发中心;北京航空航天大学航空发动机气动热力国家级重点实验室;
【分类号】：V231.1
【正文快照】： 1引言为了提高发动机的推重比,涡轮进口温度越来越高,推重比为10的航空发动机涡轮进口温度已接近2000K,如此高的温度必然会导致涡轮叶片工作的可靠性差、使用寿命短的弊端[1]。因此,必须采用一定的冷却措施,以降低涡轮叶片的温度,减小热负荷。带肋回转通道是应用于涡轮叶片中

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