复合材料风扇叶片结构预变形设计研究

发布时间：2018-05-15 13:21

本文选题：预变形设计 + 复合材料　；参考：《华侨大学》2016年硕士论文

【摘要】：传统的飞机发动机风扇叶片设计方法,虽然有很多优点,但是不可避免的都是根据工作环境来设计叶片。在工作过程中,叶型在气动力和离心力的共同作用下会产生变形,导致叶型发生偏差,与原始设计工作叶型不符,所以要对叶片进行预变形设计分析,以保证风扇叶片在实际运行的尺寸和原始设计的尺寸一致或者趋近一致。近些年,复合材料在航空发动机上的应用是目前一个全新的研究方向。复合材料因其比强度大,比刚度高,疲劳性能好,可设计其内部纤维的含量和内部结构的铺设方式等优秀条件,逐渐取代了原本金属基材料的地位,成为航空发动机风扇叶片的重要材料之一,因而研究复合材料风扇叶片预变形设计具有重要的现实意义。本文综合使用UG NX、Visual Studio2010、ANSYS、C/C++编程语言和APDL语言,完成叶片的参数化建模、复合材料工程弹性系数的设定以及预变形迭代算法的运行。具体研究内容如下:(1)利用UG/Open API函数和Menuscript模块,依靠C/C++编程语言的支持,在VS2010的编译器中,完成了对复合材料风扇叶片的参数化建模。从关键点的导入到叶片截面线的建立再到整体叶身的创建全部由程序代码自动运行,实现了从点到线再到面的三维参数化建模,为后续的有限元分析奠定了基础。(2)根据叶片的工作情况以及力学性能要求,采用各向异性复合材料(HT3/5224)作为风扇叶片的材料,用ANSYS软件完成叶片相关工程弹性系数的设定,应用SOLID46单元在叶片模型中建立层合板结构,最后将气动力和离心力加载到叶片模型上,完成变形分析。(3)使用APDL语言,提取原始叶型和变形之后的叶型之间的位移差值,采用反向叠加的方法进行节点位移之间的迭代计算,叠加位移之后的模型和原始设计模型的最大位移差值在第1次迭代之后为0.1994mm,在15次迭代计算之后,最大位移差值的数量级已经下降到10-8(mm)单位,结果表明,在10-6(mm)单位的时候,对于空间上节点坐标来说已经达到了收敛的条件,说明得到的预变形模型满足设计要求。综上所述,本文完成了复合材料风扇叶片的参数化建模、相关复合材料工程弹性系数的设定、气动离心载荷插值、迭代计算位移差值和预变形设计叶型。对复合材料风扇叶片的设计有着一定的参考价值。
[Abstract]:Although there are many advantages in the traditional design method of aeroengine fan blade, it is inevitable to design the blade according to the working environment. In the working process, the blade shape will be deformed under the combined action of aerodynamic force and centrifugal force, which will lead to the deviation of the blade shape, which does not conform to the original design of the working blade shape, so the pre-deformation design analysis of the blade should be carried out. To ensure that the fan blade in the actual operation of the size and the original design of the same or close to the same. In recent years, the application of composite materials in aeroengine is a new research direction. Because of its high specific strength, high specific stiffness and good fatigue properties, composite materials can be designed for the content of internal fibers and the laying way of internal structures, gradually replacing the status of the original metal-based materials. As one of the most important materials for aero-engine fan blades, it is of great practical significance to study the pre-deformation design of composite fan blades. In this paper, using UG NXX Visual Studio 2010 C / C programming language and APDL language, the parametric modeling of blade, the setting of elastic coefficient of composite engineering and the operation of predeformation iterative algorithm are completed. The specific research contents are as follows: (1) using UG/Open API function and Menuscript module and supported by C / C programming language, the parameterized modeling of composite fan blade is completed in the compiler of VS2010. From the introduction of the key point to the establishment of the blade section line to the creation of the whole blade body, the program code runs automatically, which realizes the 3D parameterized modeling from point to line to plane. It lays the foundation for the subsequent finite element analysis. (2) according to the working condition of the blade and the requirement of the mechanical properties, the anisotropic composite material HT3 / 5224) is used as the material of the fan blade, and the elastic coefficient of the blade related engineering is set by ANSYS software. The laminated plate structure was built by SOLID46 element in the blade model. Finally, the aerodynamic force and centrifugal force were loaded into the blade model, and the deformation analysis was completed. Using APDL language, the displacement difference between the original leaf shape and the deformed leaf shape was extracted. The maximum displacement difference between the superposition model and the original design model is 0.1994mm after the first iteration, and after 15 iterations, the maximum displacement difference between the superposition model and the original design model is 0.94 mm after the first iteration. The order of magnitude of the maximum displacement difference has been reduced to 10-8 mm) units. The results show that the convergence condition has been reached for the coordinates of nodes in space at 10-6 mm) units, indicating that the pre-deformation model can meet the design requirements. To sum up, the parametric modeling of composite fan blade, the setting of elastic coefficient of composite material engineering, the interpolation of aerodynamic centrifugal load, the iterative calculation of displacement difference and the pre-deformation design of blade profile are completed in this paper. It has certain reference value for the design of composite fan blade.
【学位授予单位】：华侨大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V232.4

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