本文關(guān)鍵詞： 紅外 邊界層轉(zhuǎn)捩 離散粗糙元 轉(zhuǎn)子葉片　出處：《空氣動(dòng)力學(xué)學(xué)報(bào)》2016年01期 　論文類(lèi)型：期刊論文

【摘要】：針對(duì)直升機(jī)轉(zhuǎn)子葉片模型表面離散粗糙元誘發(fā)邊界層轉(zhuǎn)捩問(wèn)題開(kāi)展了實(shí)驗(yàn)研究,分析不同雷諾數(shù)下粗糙元尺寸參數(shù)對(duì)轉(zhuǎn)捩位置的影響。實(shí)驗(yàn)在中航工業(yè)氣動(dòng)院直升機(jī)轉(zhuǎn)子葉片模擬裝置進(jìn)行,在模型轉(zhuǎn)子葉片表面布置不同尺寸的離散柱狀粗糙元,利用紅外熱像技術(shù)探測(cè)邊界層轉(zhuǎn)捩,并提出一種基于湍流/層流區(qū)域面積比的轉(zhuǎn)捩位置判定準(zhǔn)則,目的是實(shí)現(xiàn)邊界層轉(zhuǎn)捩位置自動(dòng)識(shí)別,進(jìn)而分析粗糙元尺寸參數(shù)對(duì)轉(zhuǎn)捩位置的影響。實(shí)驗(yàn)轉(zhuǎn)速為300至600r/m,對(duì)應(yīng)葉尖切向速度為25~40m/s。實(shí)現(xiàn)了對(duì)旋轉(zhuǎn)葉片邊界層轉(zhuǎn)捩位置的定量測(cè)量,通過(guò)實(shí)驗(yàn)驗(yàn)證,轉(zhuǎn)捩位置判定算法正確可靠,初步得到了不同高度DRE誘發(fā)轉(zhuǎn)捩位置與雷諾數(shù)之間的關(guān)系,隨著粗糙元高度的增加,轉(zhuǎn)捩位置逐漸靠前。
[Abstract]:An experimental study on boundary layer transition induced by discrete rough element on rotor blade surface of helicopter is carried out. The influence of the size parameters of rough elements on the transition position is analyzed under different Reynolds numbers. The experiment is carried out in the rotor blade simulation device of the helicopter in the Air China Industrial Pneumatic Institute. Discrete cylindrical rough elements with different sizes are arranged on the blade surface of the model rotor. The infrared thermal imaging technique is used to detect the boundary layer transition, and a transition location criterion based on the area ratio of turbulent / laminar flow region is proposed. The purpose of this paper is to realize automatic boundary layer transition location identification and to analyze the effect of the size parameters of rough element on transition position. The experimental rotational speed is 300 ~ 600r / m. The corresponding tip tangential velocity is 25 ~ 40 m / s. The quantitative measurement of the transition position of the boundary layer of the rotating blade is realized. The experimental results show that the algorithm for determining the transition position is correct and reliable. The relationship between transition location and Reynolds number induced by DRE at different heights was preliminarily obtained. With the increase of the height of rough elements, the transition position gradually moved forward.
【作者單位】： 中國(guó)航空工業(yè)空氣動(dòng)力研究院高速高雷諾數(shù)航空科技重點(diǎn)實(shí)驗(yàn)室;
【分類(lèi)號(hào)】：V211.52
【正文快照】： 0引言邊界層轉(zhuǎn)捩問(wèn)題一直以來(lái)都是理論和工程應(yīng)用研究的熱點(diǎn)話題。通常使用縮比模型對(duì)直升機(jī)螺旋槳進(jìn)行氣動(dòng)力實(shí)驗(yàn)研究,由于存在尺度效應(yīng),實(shí)驗(yàn)?zāi)Ｐ瓦吔鐚愚D(zhuǎn)捩位置與全尺寸情況下不同。導(dǎo)致實(shí)驗(yàn)測(cè)量的一些氣動(dòng)力系數(shù)存在誤差,例如懸停效率、力矩系數(shù)等[1]。因此需要采用固定轉(zhuǎn)，

本文編號(hào)：1461963