CAJ | 학술논문

动量叶素法（blade element momentum，BEM）和计算流体力学方法（computational fluid dynamics，CFD）是预测风力机气动性能的常用方法，本文基于商用MATLAB和CFX软件，对MEXICO（Model Experiments In Controlled Conditions）风轮5种风速的轴向入流工况分别采用BEM和CFD方法进行气动性能预测，其中BEM方法计算时采用Shen叶尖修正，CFD方法选用SST紊流模型求解三维雷诺时均方程。研究表明，BEM和CFD方法计算的攻角最大相对误差分别为-0.402、0.099，试验获得的来流攻角沿叶片径向分布基本处于2种方法获得的结果之间，且在叶尖处更接近CFD计算的结果；试验获得的叶片轴向力沿叶片径向分布与2种方法的预测结果基本吻合，BEM和CFD 2种方法计算的轴向力最大相对误差分别为-0.139、-0.096，当叶片进入失速状态后，BEM方法计算的切向力最大相对误差达到-0.471，表明BEM方法的预测精度有待进一步提高，研究成果可为工程模型的修正与开发提供参考。
동량협소법（blade element momentum，BEM）화계산류체역학방법（computational fluid dynamics，CFD）시예측풍력궤기동성능적상용방법，본문기우상용MATLAB화CFX연건，대MEXICO（Model Experiments In Controlled Conditions）풍륜5충풍속적축향입류공황분별채용BEM화CFD방법진행기동성능예측，기중BEM방법계산시채용Shen협첨수정，CFD방법선용SST문류모형구해삼유뢰낙시균방정。연구표명，BEM화CFD방법계산적공각최대상대오차분별위-0.402、0.099，시험획득적래류공각연협편경향분포기본처우2충방법획득적결과지간，차재협첨처경접근CFD계산적결과；시험획득적협편축향력연협편경향분포여2충방법적예측결과기본문합，BEM화CFD 2충방법계산적축향력최대상대오차분별위-0.139、-0.096，당협편진입실속상태후，BEM방법계산적절향력최대상대오차체도-0.471，표명BEM방법적예측정도유대진일보제고，연구성과가위공정모형적수정여개발제공삼고。
The aerodynamic performance of the MEXICO (Model EXperiments In Controlled cOnditions) rotor at five tunnel wind speeds is predicted by making use of BEM and CFD methods, respectively, using commercial MATLAB and CFD software. Due to the pressure differences on both sides of the blade, the tip-flow will produce secondary flow along the blade, consecutively resulting in decreases of torque. To overcome the above-mentioned issue, a variety of tip-correction models are developed, while most models overestimate the axial and tangential forces. To optimize accuracy, a new correction model summarized from CFD results by Shen is adopted in this paper. In order to accurately simulate the separation point and the separation area which is caused by the adverse pressure gradient, the CFD method using SST turbulence model is used to solve the three-dimensional Reynolds averaged equations. The first order upwind is used for the advection schemes, and the discrete equations are solved with simple algorithms. In addition, uniform velocity and static temperature are given as inlet boundary conditions, and static pressure is given as the circumferential outer boundary condition and the outlet boundary condition. The boundaries of fan-shaped both sides are defined as rotationally periodic connection, and the freeze rotor model is applied at the interface of the rotating and stationary domains, which means the relative position of rotating and stationary domains is fixed when calculating the flow field. Speed no-slip conditions are applied to solid walls such as blades. In this paper, two different meshing methods are used to generate a hexahedral grid for the rotating domain and a tetrahedral grid for stationary domain, between which comparison of the deviation of axial force on 60%blade cross section under the design condition (Vtun=15 m/s) leads to a clear decision of the better mesh method with less deviation. Taking the better mesh method into consideration, the final number of rotating domain grids is calculated according to verification of grid independence, with an amount of 2,961,385. The conclusion of this paper will be illustrated from the following points:first, the comparison of the calculated and the experimental angle of attack distribution along the span direction shows that the maximum relative errors of the attack angle calculated by BEM and CFD respectively are-0.402 and 0.099;it further illustrates that the experimental results are substantially between the results obtained by the two methods, and closer to the result of CFD at the blade tip. Meanwhile, the axial force on the blade increases with increasing radius, while the tangential force shows small change. All of the axial and tangential force in each section increases with increasing wind speed. Additionally, the maximum relative errors of axial force calculated by BEM and CFD respectively are-0.139 and-0.096. In a word, the experimental data are in good agreement with the results calculated by BEM and CFD, confirming the reliability of the MEXICO data. Second, the SST turbulence model can better capture the flow separation on the blade and has high aerodynamic performance prediction accuracy for a horizontal axis wind turbine in axial inflow conditions. Finally, the comparisons of the axial and tangential forces as well as the contrast of the angle of attack indicate that the prediction accuracy of BEM method is high when the blade is not in the stall condition. However, the airfoil characteristic becomes unstable in the stall condition, and the maximum relative error of tangential force calculated by BEM is-0.471. As a result, prediction accuracy of the BEM method needs to be further improved.