【摘要】：離心壓氣機葉輪是微型渦噴發(fā)動機的核心部件,其設計水平直接影響著微型渦噴發(fā)動機的整體性能。隨著計算機技術的發(fā)展,計算流體力學(CFD)方法、有限元分析及多軸數(shù)控加工等現(xiàn)代分析制造技術在壓氣機葉輪研究領域得到廣泛應用,但壓氣機葉輪幾何模型作為上述研究方法的基礎,其參數(shù)化造型軟件的開發(fā)卻很不成熟。因此,開發(fā)壓氣機葉輪參數(shù)化造型軟件,對于縮短微型渦噴發(fā)動機的研制周期具有重要意義。 非均勻有理B樣條(NURBS)技術在近幾年得到快速發(fā)展,本文結合壓氣機葉輪結構特點,研究了NURBS在直紋面壓氣機葉輪設計中的應用,通過NURBS給定壓氣機葉輪的幾何參數(shù)分布,進行交互式造型系統(tǒng)設計。利用C語言進行UG二次開發(fā),完成壓氣機葉輪造型系統(tǒng)程序編制與功能實現(xiàn)。 利用造型系統(tǒng)對某型渦噴發(fā)動機壓氣機葉輪進行三維造型設計。采用數(shù)值方法對壓氣機葉輪進行多工況流場計算,得到其流量特性曲線,分析壓氣機葉輪的不同工作狀態(tài)下的性能參數(shù)。對三種不同內切圓分布規(guī)律的壓氣機葉輪模型,通過計算比較了最大轉速工況下的流量特性曲線,結果表明通過合理設計子午面形狀可以改善壓氣機葉輪的效率,能大幅提高壓氣機葉輪的阻塞流量,是增大壓氣機葉輪穩(wěn)定工作范圍的一種有效方法。隨后對壓氣機葉輪進行了五軸數(shù)控加工編程,通過合理選擇驅動方式以及控制刀軸矢量方向,成功生成了刀位軌跡文件。加工仿真結果未發(fā)現(xiàn)干涉現(xiàn)象,五軸數(shù)控加工方法加工的壓氣機葉輪具有良好的表面質量。 通過對造型系統(tǒng)設計的壓氣機葉輪進行流場計算和加工仿真,結果表明本文開發(fā)的壓氣機葉輪造型系統(tǒng)的可行性和正確性,可用于壓氣機葉輪的造型設計,縮短壓氣機葉輪的研制周期。
[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.
【學位授予單位】：南京理工大學
【學位級別】：碩士
【學位授予年份】：2013
【分類號】：TH452

【參考文獻】

相關期刊論文 前10條

1 楊策,胡遼平,買靖東,老大中,王航;兩個離心壓氣機葉輪的設計與性能比較[J];北京理工大學學報;2004年09期

2 孫濤;王毅;王曉放;謝蓉;馬震岳;;變厚度葉片對離心壓縮機結構強度和性能影響[J];大連理工大學學報;2012年01期

3 楊策,馬朝臣,老大中;幾何參數(shù)變化對離心壓氣機性能影響的仿真研究[J];動力工程;2002年04期

4 陳宏冀;子午流道Bézier曲線造型中的幾何問題[J];工程熱物理學報;1997年04期

5 肖翔,趙曉路;離心壓氣機子午流道的快速設計分析[J];工程熱物理學報;2000年01期

6 劉瑞韜,徐忠;葉片數(shù)及分流葉片位置對壓氣機性能的影響[J];工程熱物理學報;2004年02期

7 初雷哲;杜建一;黃典貴;趙曉路;徐建中;;離心壓氣機葉片前緣幾何形狀對性能的影響[J];工程熱物理學報;2008年05期

8 陸宏志,徐力平,方韌;壓氣機葉片前緣形狀的改進設計[J];航空動力學報;2000年02期

9 田寶林;世界無人機和巡航導彈用發(fā)動機發(fā)展概況[J];航空發(fā)動機;2003年04期

10 田慶;莫蓉;夏禹;汪文虎;;航空發(fā)動機葉片CAD造型方法[J];航空制造技術;2007年02期

相關博士學位論文 前1條

1 董穎懷;一種微型渦輪發(fā)動機的關鍵結構及其制造技術的研究[D];哈爾濱工業(yè)大學;2009年

相關碩士學位論文 前3條

1 萬東;基于NURBS的葉片設計CAD系統(tǒng)軟件的開發(fā)研究[D];西北工業(yè)大學;2003年

2 孟軍強;基于NURBS的渦輪葉片造型技術研究[D];南京航空航天大學;2007年

3 莊偉娜;整體葉輪實體造型與五坐標數(shù)控加工技術研究[D];南京航空航天大學;2008年

，

本文編號：2481688