本文關(guān)鍵詞： 單勺進(jìn)氣道 環(huán)形截面設(shè)計(jì)方法 可視化造型軟件 總壓恢復(fù)系數(shù) 總壓畸變指數(shù) 滑移網(wǎng)格 螺旋槳滑流　出處：《南京航空航天大學(xué)》2016年碩士論文　論文類型：學(xué)位論文

【摘要】：上世紀(jì)70年代以來,螺旋槳飛機(jī)由于推進(jìn)效率高和經(jīng)濟(jì)性好等優(yōu)點(diǎn)而重新受到重視與發(fā)展。由于結(jié)構(gòu)上的兼容性要求,使其進(jìn)氣道幾何型面設(shè)計(jì)具有一定難度。結(jié)構(gòu)特殊性加上螺旋槳滑流影響使進(jìn)氣道流場復(fù)雜化,因此快速參數(shù)化設(shè)計(jì)出性能良好的渦槳進(jìn)氣道具有重要意義。本文采用唇冠到唇脊變厚度唇口設(shè)計(jì);基于環(huán)形截面方法設(shè)計(jì)主通道,設(shè)計(jì)幾何特征參數(shù)沿通道變化規(guī)律,改造S型曲線公式以適用渦槳進(jìn)氣道中心線設(shè)計(jì)要求,提出擴(kuò)展角采用Nurbs曲線變化規(guī)律。并根據(jù)單勺進(jìn)氣道設(shè)計(jì)算法,在Nussyppag體系下編程開發(fā)了單勺進(jìn)氣道可視化造型軟件TurboPropInlet。針對設(shè)計(jì)馬赫為0.5的單勺進(jìn)氣道模型,本文研究了幾何參數(shù)對單勺進(jìn)氣道性能的影響,主要結(jié)論如下:唇脊收縮比對唇口設(shè)計(jì)性能影響大于唇冠收縮比;進(jìn)出口偏距越大或喉道擴(kuò)展角越大,出口總壓畸變指數(shù)越大;主通道采用先擴(kuò)張后收縮方式能很大程度上減小出口總壓畸變指數(shù)。優(yōu)選模型設(shè)計(jì)性能良好,設(shè)計(jì)狀態(tài)下總壓恢復(fù)系數(shù)為0.9864,總壓畸變指數(shù)DC(60)?為0.0912。優(yōu)選模型在較大流量范圍和飛行馬赫內(nèi)性能良好;在小于?15的攻角和側(cè)滑角范圍內(nèi)性能下降幅度小。上述研究結(jié)論對于渦槳進(jìn)氣道設(shè)計(jì)和性能分析有一定指導(dǎo)意義。本文最后基于滑移網(wǎng)格技術(shù)研究了低速起飛狀態(tài)下滑流對渦槳進(jìn)氣道性能的影響,為以后深入進(jìn)行螺旋槳滑流影響研究打下了一定基礎(chǔ)。
[Abstract]:Since -30s, propeller aircraft has been revalued and developed because of its high propulsion efficiency and good economy. It is difficult to design the geometric plane of the inlet. The special structure and the influence of the propeller slip make the flow field of the inlet more complicated. Therefore, it is of great significance to design a fast parameterized impeller inlet with good performance. In this paper, the lip design from lip crown to lip ridge with variable thickness is adopted. The main passage is designed based on the annular section method. The variation law of geometric characteristic parameters along the channel is designed, and the S-shape curve formula is modified to meet the design requirements of the center line of the propeller inlet. The expansion angle is changed by Nurbs curve, and the algorithm is designed according to the single scoop inlet. The visual modeling software Turbo Prop Inlet is developed under the Nussyppag system. A single-scoop inlet model with Mach 0.5 is designed. The effects of geometric parameters on the performance of a single spoon inlet are studied in this paper. The main conclusions are as follows: the effect of lip ridge contraction ratio is greater than that of lip crown contraction ratio; The larger the deviation between the inlet and outlet or the larger the throat expansion angle, the greater the total pressure distortion index of the outlet. The main channel can reduce the total pressure distortion index to a great extent by first expanding and then contracting. The optimal selection model has good design performance and the total pressure recovery coefficient is 0.9864 in the design state. Total pressure distortion index DCU 60? The optimal selection model has good performance in large flow range and flight Mach. The results above are helpful for the design and performance analysis of the propeller inlet. Finally, based on the sliding grid technique, the paper studies the low-speed take-off state based on the slip-grid technique, which is helpful to the design and performance analysis of the propeller inlet in the range of the angle of attack and the sideslip angle. The influence of slip flow on the performance of propeller inlet. It lays a foundation for further research on the influence of propeller slip flow.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2016
【分類號】：V211.48

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