CAJ | 학술논문

以某1．5 MW 风机叶片 S818翼型为研究对象，建立了翼型流场有限元分析模型。采用基于 Reynolds 平均的 Navier-Stokes 不可压缩粘性方程作为流动控制方程，对无冰翼型、霜冰、弦长冰及角冰翼型进行数值模拟分析，得到了－2°－20°攻角下不同厚度叶片翼型的升阻比、速度矢量和表面压力分布。研究结果表明：覆冰越厚，翼型的最大升阻比降幅越大。对于弦长冰和角冰在厚度达到一定值时，使得升阻比损失产生较大的突变。在覆冰厚度都为10 mm 时，角冰的最大升阻比减幅最大，达到22．04％；其次是弦长冰为11．97％，霜冰的最小为6．41％。同时结冰后的翼型会提前进入失速区，导致桨叶气动性能恶化，降低了风机的功率系数。
이모1．5 MW 풍궤협편 S818익형위연구대상，건립료익형류장유한원분석모형。채용기우 Reynolds 평균적 Navier-Stokes 불가압축점성방정작위류동공제방정，대무빙익형、상빙、현장빙급각빙익형진행수치모의분석，득도료－2°－20°공각하불동후도협편익형적승조비、속도시량화표면압력분포。연구결과표명：복빙월후，익형적최대승조비강폭월대。대우현장빙화각빙재후도체도일정치시，사득승조비손실산생교대적돌변。재복빙후도도위10 mm 시，각빙적최대승조비감폭최대，체도22．04％；기차시현장빙위11．97％，상빙적최소위6．41％。동시결빙후적익형회제전진입실속구，도치장협기동성능악화，강저료풍궤적공솔계수。
Taking the S818 airfoil of 1.5 MW wind turbine blade as the research object.Model of the finite ele-ment of airfoil flow field was built in this paper.The non-viscous incompressible Navier-stokes equations are used as flow control equation,which conducted numerical simulation analysis on Ice-free airfoil,airfoil of rime ice, chord-length ice,and horn ice.The pressure distribution are obtained from the lift-drag ratio,velocity vector and surface pressure of different thickness of the blade airfoil in the angle of attack from -2°to 20°.The results showed that the thicker of the ice coating,the shaper maximum lift-drag ratio of airfoil are decreased.Moreover, certain thickness of chord length ice and horn ice leads to the mutation of the loss of lift-drag ratio.When ice thickness is 10 mm,the maximum lift-drag ratio amplitude reduction of horn ice reached the maximum at 22.04%,the chord length ice at 11.97% and rime ice at 6.14%.In addition,the airfoil after icing would enter stall area in advance which deteriorates aerodynamic performance of blade and reduces the power coefficient of wind turbine.