【摘要】：隨著風(fēng)力機(jī)的快速發(fā)展,氣動(dòng)噪聲問(wèn)題已經(jīng)成為其重要制約因素之一,對(duì)于風(fēng)力機(jī)噪聲問(wèn)題的研究必將成為風(fēng)力機(jī)發(fā)展過(guò)程中的重要議題。為了研究風(fēng)力機(jī)氣動(dòng)噪聲,本文選取了風(fēng)力機(jī)專用翼型S809翼型作為研究模型,利用半經(jīng)驗(yàn)算法和計(jì)算流體力學(xué)與計(jì)算氣動(dòng)聲學(xué)相結(jié)合的方法預(yù)測(cè)翼型的噪聲,主要是尾緣噪聲產(chǎn)生過(guò)程和傳播特性。偏轉(zhuǎn)翼型的尾緣會(huì)使翼型的氣動(dòng)性能產(chǎn)生變化,同時(shí)對(duì)流經(jīng)翼型的氣動(dòng)噪音也會(huì)產(chǎn)生一定影響。為評(píng)價(jià)翼型尾緣偏轉(zhuǎn)對(duì)氣動(dòng)性能和氣動(dòng)噪音的影響水平,本文采用NASA基于充足聲學(xué)實(shí)驗(yàn)結(jié)果而得的翼型自噪聲方法進(jìn)行建模。選取S809翼型為研究模型,翼型的升阻比和氣動(dòng)噪聲為優(yōu)化目標(biāo),優(yōu)化其尾緣偏轉(zhuǎn)的弦向位置和偏轉(zhuǎn)角度,從而得到設(shè)計(jì)迎角下兼顧氣動(dòng)性能和氣動(dòng)噪聲的尾緣變化方案,同時(shí)為了驗(yàn)證優(yōu)化后的效果,本文將優(yōu)化結(jié)果應(yīng)用于NREL直徑10m的真實(shí)葉片,得到了與翼型優(yōu)化相同的結(jié)果。在氣動(dòng)噪聲數(shù)值模擬方面,本文采用LES/FW-H相結(jié)合的方法對(duì)NACA0018和S809翼型的流動(dòng)和發(fā)聲進(jìn)行非定常數(shù)值模擬研究,獲得了相應(yīng)的流場(chǎng)和聲場(chǎng)的計(jì)算結(jié)果,并對(duì)尾緣噪聲特性進(jìn)行了分析。在此基礎(chǔ)上,本文對(duì)鈍尾緣的S809翼型的氣動(dòng)噪聲特性進(jìn)行了設(shè)計(jì)分析,給出鈍尾緣對(duì)風(fēng)力機(jī)翼型氣動(dòng)噪聲的影響。
[Abstract]:With the rapid development of wind turbine, the problem of aerodynamic noise has become one of its important constraints, and the research on the noise of wind turbine will be an important issue in the development of wind turbine. In order to study the aerodynamic noise of the wind turbine, the special airfoil S809 airfoil for wind turbine is selected as the study model, and the noise of the airfoil is predicted by means of the semi-empirical algorithm and the method of combining the computational fluid dynamics with the calculation of the aerodynamic acoustics, which is mainly the process and propagation characteristics of the trailing edge noise. The trailing edge of the deflected airfoil results in a change in the aerodynamic performance of the airfoil, while the aerodynamic noise flowing through the airfoil will also have a certain impact. In order to evaluate the effect of the airfoil trailing edge deflection on the aerodynamic performance and aerodynamic noise, an airfoil self-noise method based on the results of sufficient acoustic experiments was used to model the aerodynamic performance and aerodynamic noise. The S809 airfoil is selected as the study model, the lift-drag ratio and the aerodynamic noise of the airfoil are the optimization targets, the chord-to-chord position and the deflection angle of the tail edge deflection are optimized, the tail edge change scheme of the aerodynamic performance and the pneumatic noise is taken into consideration at the design angle of attack, and meanwhile, in order to verify the optimized effect, The optimization results are applied to the real blades of the NREL diameter of 10 m, and the same results as the airfoil optimization are obtained. In the aspect of the numerical simulation of aerodynamic noise, the unsteady numerical simulation of the flow and sound of the airfoil of the NACA0018 and S809 is studied by using the combination of LES/ FW-H, and the results of the corresponding flow field and sound field are obtained, and the noise characteristics of the trailing edge are analyzed. On this basis, the aerodynamic noise characteristics of the S809 airfoil of the blunt trailing edge are analyzed, and the effect of the blunt trailing edge on the aerodynamic noise of the wind turbine is given.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2014
【分類號(hào)】：TM315
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本文編號(hào)：2438393