航空发动机典型板材成形性能数据库及选材评价系统开发

发布时间：2018-12-12 15:35

【摘要】：航空发动机钣金件与航空发动机各部件一样,需承受温度、载荷、环境介质等严酷工作条件,铝合金、钛合金、高温合金等板材是适宜的制造材料。随着先进航空发动机制造要求的不断提高,数字化精密成形已成为航空发动机钣金件成形的必然发展趋势。目前,国内航空发动机钣金件成形制造中由于缺少常用的典型板材的成形性能基础数据,而直接影响数字化精密钣金件成形的实施。因此,研究航空发动机材料的成形性能,构建选材评价系统对满足我国航空发动机钣金件精密制造中成形工艺基础数据要求及合理选材具有重要的意义。本文针对航空发动机用典型板材成形性能数据库、选材评价系统开发等问题进行了深入研究。在分析航空发动机用典型板材类型的材料特性的基础上,基于国际通用模式及钣金成形工艺要求,阐述了板材成形性能的指标、表征及测试方法。以航空发动机典型材料GH605高温合金和Ti-230钛合金为例进行了包括单向拉伸试验、模拟成形性能试验以及FLD试验等的成形性能试验研究,得到了其本构方程以及屈服强度、抗拉强度、延伸率、塑性应变比等基本成形性能参数;由模拟成形性能试验得到了其极限拉深比、扩孔率、杯突值、最小相对弯曲半径等模拟成形性能参数;由FLD试验得到了其成形极限图,为板材断裂失稳判据提供了依据。此外,整合了本课题组积累的由试验得到的包括铝合金、钛合金及高温合金等成形性能数据,为有限元分析、板材成形性能数据库及选材评价系统的构建提供了基本数据支持。基于航空发动机钣金件精密成形工艺实施时的成形性及选材合理性要求,进行了成形性能数据库系统总体设计、信息合理分类、设计表的内容及数据库总体内容;并对选材库进行系统分析,确定了选材评价规则。在Visual Studio 2012开发平台上采用C#语言结合SQL Server 2008数据库软件完成了航空发动机典型板材成形性能数据库及选材评价系统的开发。开发的系统前台界面可以对材料信息进行便利的查询、搜索以及对典型发动机零件选材评价;系统后台管理中通过设置管理员与用户权限,实现对数据库有序的更新、管理,使得系统能够较好的应用在实际的生产中。通过以上的研究工作,本文取得了如下成果:(1)基于成形性能试验结果,开发了包括铝合金、钛合金、高温合金及不锈钢四类航空发动机用总计29种不同厚度规格的典型板材的成形性能数据库及选材评价系统,该数据库与商用有限元分析软件Dynaform的材料库实现了共享。(2)开发的成形性能数据库,可为航空发动机钣金件精密成形的工艺设计及成形过程的有限元模拟仿真分析提供相关材料成形性能数据支持及判据。(3)开发的成形性能数据库及选材评价系统已成功应用于某型航空发动机钣金件的精密成形的生产。
[Abstract]:The sheet metal parts of aero-engine are the same as the components of aeroengine, which need to bear the harsh working conditions, such as temperature, load, environmental medium and so on. Aluminum alloy, titanium alloy, superalloy and other plates are suitable manufacturing materials. With the development of advanced aero-engine manufacturing, digital precision forming has become an inevitable trend of aero-engine sheet metal forming. At present, the domestic aero-engine sheet metal forming manufacturing, due to the lack of common typical sheet metal forming performance basic data, which directly affects the digital precision sheet metal forming implementation. Therefore, it is of great significance to study the formability of aero-engine materials and build a material selection and evaluation system to meet the basic data requirements and reasonable material selection in the precise manufacture of aeroengine sheet metal parts in China. In this paper, the forming performance database of typical sheet metal for aeroengine and the development of material selection evaluation system are studied. Based on the analysis of the material characteristics of typical sheet metal types for aero-engine, and based on the international general pattern and sheet metal forming process requirements, the index, characterization and testing method of sheet metal formability are described. Taking GH605 superalloy and Ti-230 titanium alloy as examples, the formability tests including uniaxial tensile test, simulated formability test and FLD test were carried out. The constitutive equation and yield strength were obtained. Tensile strength, elongation, plastic strain ratio and other basic forming performance parameters; The forming performance parameters such as ultimate drawing ratio, hole expansion ratio, cup burst value and minimum relative bending radius are obtained from the simulation formability test, and the forming limit diagram is obtained by FLD test, which provides the basis for the fracture instability criterion of sheet metal. In addition, the experimental data including aluminum alloy, titanium alloy and superalloy are integrated, which provides the basic data support for finite element analysis, sheet forming property database and material selection evaluation system. Based on the requirements of formability and material selection of aeroengine sheet metal parts precision forming process, the overall design of forming performance database system, the reasonable classification of information, the content of design table and the overall content of database are carried out. A systematic analysis of the material selection library was carried out, and the rules of material selection evaluation were determined. The database of typical sheet metal forming performance and material selection evaluation system of aero-engine are developed on the platform of Visual Studio 2012 by using C # language and SQL Server 2008 database software. The system foreground interface can be used to query, search and evaluate the material information of typical engine parts. In the background management of the system, by setting the administrator and user authority, the database can be updated and managed in an orderly way, which makes the system better applied in actual production. The results are as follows: (1) based on the results of formability test, aluminum alloy and titanium alloy are developed. The formability database and material selection evaluation system of 29 typical sheet metal with different thickness specifications for four kinds of aeroengines of superalloy and stainless steel. The database is shared with the material library of commercial finite element analysis software Dynaform. (2) the formability database is developed. It can provide data support and criterion for precision forming process design and finite element simulation analysis of aero-engine sheet metal parts. (3) the formability database and material selection evaluation are developed. The system has been successfully used in the production of a certain aeroengine sheet metal parts precision forming.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V263

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