基于UG的压气机叶轮造型系统设计研究

发布时间：2019-05-20 13:46

【摘要】：离心压气机叶轮是微型涡喷发动机的核心部件,其设计水平直接影响着微型涡喷发动机的整体性能。随着计算机技术的发展,计算流体力学(CFD)方法、有限元分析及多轴数控加工等现代分析制造技术在压气机叶轮研究领域得到广泛应用,但压气机叶轮几何模型作为上述研究方法的基础,其参数化造型软件的开发却很不成熟。因此,开发压气机叶轮参数化造型软件,对于缩短微型涡喷发动机的研制周期具有重要意义。非均匀有理B样条(NURBS)技术在近几年得到快速发展,本文结合压气机叶轮结构特点,研究了NURBS在直纹面压气机叶轮设计中的应用,通过NURBS给定压气机叶轮的几何参数分布,进行交互式造型系统设计。利用C语言进行UG二次开发,完成压气机叶轮造型系统程序编制与功能实现。利用造型系统对某型涡喷发动机压气机叶轮进行三维造型设计。采用数值方法对压气机叶轮进行多工况流场计算,得到其流量特性曲线,分析压气机叶轮的不同工作状态下的性能参数。对三种不同内切圆分布规律的压气机叶轮模型,通过计算比较了最大转速工况下的流量特性曲线,结果表明通过合理设计子午面形状可以改善压气机叶轮的效率,能大幅提高压气机叶轮的阻塞流量,是增大压气机叶轮稳定工作范围的一种有效方法。随后对压气机叶轮进行了五轴数控加工编程,通过合理选择驱动方式以及控制刀轴矢量方向,成功生成了刀位轨迹文件。加工仿真结果未发现干涉现象,五轴数控加工方法加工的压气机叶轮具有良好的表面质量。通过对造型系统设计的压气机叶轮进行流场计算和加工仿真,结果表明本文开发的压气机叶轮造型系统的可行性和正确性,可用于压气机叶轮的造型设计,缩短压气机叶轮的研制周期。
[Abstract]:Centrifugal compressor impeller is the core component of micro turbojet engine, and its design level directly affects the overall performance of micro turbojet engine. With the development of computer technology, modern analytical and manufacturing technologies, such as computational fluid dynamics (CFD) method, finite element analysis and multi-axis NC machining, have been widely used in the field of compressor impeller research. However, as the basis of the above research methods, the development of parametric modeling software for compressor impeller geometry model is very immature. Therefore, the development of compressor impeller parametric modeling software is of great significance to shorten the development cycle of micro turbojet engine. Non-uniform rational B-Spline (NURBS) technology has been developed rapidly in recent years. Based on the structural characteristics of compressor impeller, the application of NURBS in the design of ruled compressor impeller is studied in this paper. The geometric parameter distribution of compressor impeller is given by NURBS. Carry on the interactive modeling system design. The secondary development of UG is carried out with C language, and the programming and function realization of compressor impeller modeling system are completed. The three-dimensional modeling design of a turbojet engine compressor impeller is carried out by using the modeling system. The flow field of compressor impeller is calculated by numerical method, and the flow characteristic curve is obtained, and the performance parameters of compressor impeller under different working conditions are analyzed. For three compressor impeller models with different internal tangential distribution laws, the flow characteristic curves under the condition of maximum speed are calculated and compared. the results show that the efficiency of compressor impeller can be improved by reasonably designing the shape of meridian surface. It can greatly increase the blocking flow rate of compressor impeller, and it is an effective method to increase the stable working range of compressor impeller. Then the compressor impeller is programmed by five-axis NC machining, and the tool position trajectory file is successfully generated by reasonably selecting the driving mode and controlling the direction of the tool axis vector. No interference phenomenon is found in the machining simulation results. The compressor impeller machined by five-axis NC machining method has good surface quality. Through the flow field calculation and machining simulation of the compressor impeller designed by the modeling system, the results show that the compressor impeller modeling system developed in this paper is feasible and correct, and can be used in the modeling design of the compressor impeller. Shorten the development cycle of compressor impeller.
【学位授予单位】：南京理工大学
【学位级别】：硕士
【学位授予年份】：2013
【分类号】：TH452

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