【摘要】：航空發(fā)動機鈑金件與航空發(fā)動機各部件一樣,需承受溫度、載荷、環(huán)境介質(zhì)等嚴酷工作條件,鋁合金、鈦合金、高溫合金等板材是適宜的制造材料。隨著先進航空發(fā)動機制造要求的不斷提高,數(shù)字化精密成形已成為航空發(fā)動機鈑金件成形的必然發(fā)展趨勢。目前,國內(nèi)航空發(fā)動機鈑金件成形制造中由于缺少常用的典型板材的成形性能基礎(chǔ)數(shù)據(jù),而直接影響數(shù)字化精密鈑金件成形的實施。因此,研究航空發(fā)動機材料的成形性能,構(gòu)建選材評價系統(tǒng)對滿足我國航空發(fā)動機鈑金件精密制造中成形工藝基礎(chǔ)數(shù)據(jù)要求及合理選材具有重要的意義。本文針對航空發(fā)動機用典型板材成形性能數(shù)據(jù)庫、選材評價系統(tǒng)開發(fā)等問題進行了深入研究。在分析航空發(fā)動機用典型板材類型的材料特性的基礎(chǔ)上,基于國際通用模式及鈑金成形工藝要求,闡述了板材成形性能的指標、表征及測試方法。以航空發(fā)動機典型材料GH605高溫合金和Ti-230鈦合金為例進行了包括單向拉伸試驗、模擬成形性能試驗以及FLD試驗等的成形性能試驗研究,得到了其本構(gòu)方程以及屈服強度、抗拉強度、延伸率、塑性應(yīng)變比等基本成形性能參數(shù);由模擬成形性能試驗得到了其極限拉深比、擴孔率、杯突值、最小相對彎曲半徑等模擬成形性能參數(shù);由FLD試驗得到了其成形極限圖,為板材斷裂失穩(wěn)判據(jù)提供了依據(jù)。此外,整合了本課題組積累的由試驗得到的包括鋁合金、鈦合金及高溫合金等成形性能數(shù)據(jù),為有限元分析、板材成形性能數(shù)據(jù)庫及選材評價系統(tǒng)的構(gòu)建提供了基本數(shù)據(jù)支持�；诤娇瞻l(fā)動機鈑金件精密成形工藝實施時的成形性及選材合理性要求,進行了成形性能數(shù)據(jù)庫系統(tǒng)總體設(shè)計、信息合理分類、設(shè)計表的內(nèi)容及數(shù)據(jù)庫總體內(nèi)容;并對選材庫進行系統(tǒng)分析,確定了選材評價規(guī)則。在Visual Studio 2012開發(fā)平臺上采用C#語言結(jié)合SQL Server 2008數(shù)據(jù)庫軟件完成了航空發(fā)動機典型板材成形性能數(shù)據(jù)庫及選材評價系統(tǒng)的開發(fā)。開發(fā)的系統(tǒng)前臺界面可以對材料信息進行便利的查詢、搜索以及對典型發(fā)動機零件選材評價;系統(tǒng)后臺管理中通過設(shè)置管理員與用戶權(quán)限,實現(xiàn)對數(shù)據(jù)庫有序的更新、管理,使得系統(tǒng)能夠較好的應(yīng)用在實際的生產(chǎn)中。通過以上的研究工作,本文取得了如下成果:(1)基于成形性能試驗結(jié)果,開發(fā)了包括鋁合金、鈦合金、高溫合金及不銹鋼四類航空發(fā)動機用總計29種不同厚度規(guī)格的典型板材的成形性能數(shù)據(jù)庫及選材評價系統(tǒng),該數(shù)據(jù)庫與商用有限元分析軟件Dynaform的材料庫實現(xiàn)了共享。(2)開發(fā)的成形性能數(shù)據(jù)庫,可為航空發(fā)動機鈑金件精密成形的工藝設(shè)計及成形過程的有限元模擬仿真分析提供相關(guān)材料成形性能數(shù)據(jù)支持及判據(jù)。(3)開發(fā)的成形性能數(shù)據(jù)庫及選材評價系統(tǒng)已成功應(yīng)用于某型航空發(fā)動機鈑金件的精密成形的生產(chǎn)。
[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.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2016
【分類號】：V263

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