共查询到20条相似文献,搜索用时 328 毫秒
1.
2.
3.
4.
5.
6.
7.
8.
《太阳能》2021,(6)
以风电机组单叶片吊装过程中叶根螺栓的受力情况为研究对象,采用ANSYS软件中的BEAM188单元模拟叶根螺栓,利用有限元分析建立仿真模型,并进行了叶根螺栓的受力分析,将仿真结果与理论结果进行对比,确保了仿真结果的正确性与有效性;分析了不同预紧力施加方式下,叶根螺栓的应力增量、安全系数,以及接触面接触状态与开口位移的变化情况,从而得到了对叶根螺栓施加预紧力时安全且合理的方案。结果表明:在风电机组的单叶片吊装过程中,随着叶根螺栓数目的增多,其应力增量逐渐减小、安全系数增加、开口位移降低;而在单叶片的实际吊装工况下,虽然无法实现向所有叶根螺栓施加目标预紧力,但仍需安装不能施加目标预紧力的叶根螺栓,并利用扭矩扳手进行校紧,以增加叶根螺栓的安全系数,减少开口位移,保证单叶片吊装过程中的安全性与可实施性。 相似文献
9.
10.
11.
Blade Parameterization and Aerodynamic Design Optimization for a 3D Transonic Compressor Rotor 总被引:1,自引:0,他引:1
Naixing Chen Hongwu Zhang Yanji Xu Weiguang Huang Institute of Engineering Thermophysics Chinese Academy of Sciences P.O.Box Beijing CHINA.E-mail:nxc@mail.etp.ac.cn Fax: - 《热科学学报(英文版)》2007,16(2):105-114
The present paper describes an optimization methodology for aerodynamic design of turbomachinery combinedwith a rapid 3D blade and grid generator(RAPID3DGRID),a N.S.solver,a blade parameterization method(BPM),a gradient-based parameterization-analyzing method(GPAM),a response surface method(RSM)withzooming algorithm and a simple gradient method.By the use of blade parameterization method a transonic com-pressor rotor can be expressed by a set of polynomials,and then it enables us to transform coordinate-expressedblade data to parameter-expressed and then to reduce the number of parameters.With changing any one of theparameters and by applying grid generator and N.S.solver,we can obtain several groups of samples.Here onlyten parameters were considered to search an optimized compressor rotor.As a result of optimization,the adiabaticefficiency was increased by 1.73%. 相似文献
12.
The S2 flow path design method of the transonic compressor is used to design the one stage fan in order to replace the original designed blade cascade which has two-stage transonic fan rotors. In the modification design, the camber line is parameterized by a quartic polynomial curve and the thickness distribution of the blade profile is controlled by the double-thrice polynomial Therefore, the inlet flow has been pre-compressed and the location and intensity of the shock wave at supersonic area have been controlled in order to let the new blade profiles have better aerodynamic performance. The computational results show that the new single stage fan rotor increases the efficiency by two percent at the design condition and the total pressure ratio is slightly higher than that of the original design. At the same time, it also meets the mass flow rate and the geometrical size requirements for the modification design. 相似文献
13.
为了得到某燃气轮机涡轮叶片关键截面的真实寿命,设计并开展了涡轮叶片热-机械疲劳试验,获得了真实寿命数据,并基于试验结果提出了一种涡轮叶片低周疲劳与蠕变疲劳交互的寿命预测方法。首先,采用一维线弹性关系、修正公式以及循环应力应变关系3种名义应力应变处理模型计算获得了名义应变;然后,利用SWT寿命关系式预测模型预测了叶片的热-机械疲劳寿命;再将预测寿命与试验获得的真实寿命进行对比分析。研究表明:对于某型燃气轮机涡轮叶片,基于SWT预测模型的循环应力应变关系方法相比于一维线弹性关系和修正公式法预测精度最高,与试验寿命相比,预测误差在4倍分散带之内。 相似文献
14.
水平轴风力机翼型大攻角分离流动的数值模拟 总被引:10,自引:2,他引:10
翼型的失速特性是失调速节型水风力机的气动性能分析和颤振分析的基础,许多涉及这类问题的研究大多只给出了翼型刚开始失速时的计算结果,然而在正常运行工况下叶片端部翼型的深失速特性是风力机的最关键的一类问题,通过求解二维非常,可压的N-S方程计算了风力机常用翼型NACA4418的绕流特性,N-S方程在贴体坐标系中给出用Poisson方程法生成了C型网格,数值计算了采用了一种改进的LU-SGS格式。将翼型的 相似文献
15.
在燃气轮机高压涡轮叶片上安装缘板阻尼结构可以有效降低叶片振动应力,为了掌握叶片振动特性,进而指导阻尼结构设计,以某船用燃气轮机高压涡轮转子为研究对象,开展带缘板阻尼叶盘系统高速旋转激振试验。设计了缘板阻尼结构形式,开发了雾化油滴喷液激振试验系统;同时,模拟常温环境下的叶片工作载荷,结合试验数据分析获取叶片安装阻尼器前后的动应力变化情况。试验结果表明:所设计的试验系统能够很好地模拟叶片弯曲和扭转共振状态;无阻尼激振试验获取的叶片模态参数与理论计算值相当,试验结果验证了理论计算方法的准确性;安装缘板阻尼器后叶片弯曲振动应力下降明显,存在最优阻尼参数使减振效果最佳;根据叶片幅频响应曲线可以看出,缘板阻尼器使叶片非线性力学特征增强,出现叶片振动能量相互传递的现象。 相似文献
16.
《Energy》2005,30(11-12):2101-2114
This study proposes a structural design for developing a medium scale composite wind turbine blade made of E-glass/epoxy for a 750 kW class horizontal axis wind turbine system. The design loads were determined from various load cases specified at the IEC61400-1 international specification and GL regulations for the wind energy conversion system. A specific composite structure configuration, which can effectively endure various loads such as aerodynamic loads and loads due to accumulation of ice, hygro-thermal and mechanical loads, was proposed. To evaluate the proposed composite wind turbine blade, structural analysis was performed by using the finite element method. Parametric studies were carried out to determine an acceptable blade structural design, and the most dominant design parameters were confirmed. In this study, the proposed blade structure was confirmed to be safe and stable under various load conditions, including the extreme load conditions. Moreover, the blade adapted a new blade root joint with insert bolts, and its safety was verified at design loads including fatigue loads. The fatigue life of a blade that has to endure for more than 20 years was estimated by using the well-known S–N linear damage theory, the service load spectrum, and the Spera's empirical equations. With the results obtained from all the structural design and analysis, prototype composite blades were manufactured. A specific construction process including the lay-up molding method was applied to manufacturing blades. Full-scale static structural test was performed with the simulated aerodynamic loads. From the experimental results, it was found that the designed blade had structural integrity. In addition, the measured results of deflections, strains, mass, and radial center of gravity agreed well with the analytical results. The prototype blade was successfully certified by an international certification institute, GL (Germanisher Lloyd) in Germany. 相似文献
17.
18.
针对目前风电叶片形变过程中挠曲度测量误差较大的问题,提出一种基于惯性网络的相对运动监测算法。首先根据应力分析对叶片建立主从式惯性网络,然后推导出主子节点间的相对运动解算方法并建立相对导航误差模型,设计相对导航误差估计滤波器,通过误差反馈保证子节点的位姿解算精度;其次构建联邦式的相对惯性导航误差估计滤波器进行主子节点的数据融合,提高风电叶片的形变估计精度及系统整体的容错性;最后对某型风电叶片进行静力加载试验,试验结果表明:该算法可准确测量出叶片上各节点在三维空间的位移曲线,3个子节点在挥舞方向的平均相对误差仅为0.92%、1.18%、1.07%。该算法可实时监测风电叶片的位姿状态,在叶片检测及风力机日常运行的安全监测上具有较好的理论研究意义与工程应用价值。 相似文献
19.