【摘要】：離心壓氣機(jī)葉輪是微型渦噴發(fā)動(dòng)機(jī)的核心部件,其設(shè)計(jì)水平直接影響著微型渦噴發(fā)動(dòng)機(jī)的整體性能。隨著計(jì)算機(jī)技術(shù)的發(fā)展,計(jì)算流體力學(xué)(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(shù)在壓氣機(jī)葉輪研究領(lǐng)域得到廣泛應(yīng)用,但壓氣機(jī)葉輪幾何模型作為上述研究方法的基礎(chǔ),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(jī)葉輪參數(shù)化造型軟件,對(duì)于縮短微型渦噴發(fā)動(dòng)機(jī)的研制周期具有重要意義。 非均勻有理B樣條(NURBS)技術(shù)在近幾年得到快速發(fā)展,本文結(jié)合壓氣機(jī)葉輪結(jié)構(gòu)特點(diǎn),研究了NURBS在直紋面壓氣機(jī)葉輪設(shè)計(jì)中的應(yīng)用,通過NURBS給定壓氣機(jī)葉輪的幾何參數(shù)分布,進(jìn)行交互式造型系統(tǒng)設(shè)計(jì)。利用C語言進(jìn)行UG二次開發(fā),完成壓氣機(jī)葉輪造型系統(tǒng)程序編制與功能實(shí)現(xiàn)。 利用造型系統(tǒng)對(duì)某型渦噴發(fā)動(dòng)機(jī)壓氣機(jī)葉輪進(jìn)行三維造型設(shè)計(jì)。采用數(shù)值方法對(duì)壓氣機(jī)葉輪進(jìn)行多工況流場(chǎng)計(jì)算,得到其流量特性曲線,分析壓氣機(jī)葉輪的不同工作狀態(tài)下的性能參數(shù)。對(duì)三種不同內(nèi)切圓分布規(guī)律的壓氣機(jī)葉輪模型,通過計(jì)算比較了最大轉(zhuǎn)速工況下的流量特性曲線,結(jié)果表明通過合理設(shè)計(jì)子午面形狀可以改善壓氣機(jī)葉輪的效率,能大幅提高壓氣機(jī)葉輪的阻塞流量,是增大壓氣機(jī)葉輪穩(wěn)定工作范圍的一種有效方法。隨后對(duì)壓氣機(jī)葉輪進(jìn)行了五軸數(shù)控加工編程,通過合理選擇驅(qū)動(dòng)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(jié)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(jī)葉輪具有良好的表面質(zhì)量。 通過對(duì)造型系統(tǒng)設(shè)計(jì)的壓氣機(jī)葉輪進(jìn)行流場(chǎng)計(jì)算和加工仿真,結(jié)果表明本文開發(fā)的壓氣機(jī)葉輪造型系統(tǒng)的可行性和正確性,可用于壓氣機(jī)葉輪的造型設(shè)計(jì),縮短壓氣機(jī)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(xué)位授予單位】：南京理工大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2013
【分類號(hào)】：TH452

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本文編號(hào)：2481688