本文選題：預(yù)變形設(shè)計 + 復(fù)合材料　； 參考：《華僑大學(xué)》2016年碩士論文

【摘要】：傳統(tǒng)的飛機(jī)發(fā)動機(jī)風(fēng)扇葉片設(shè)計方法,雖然有很多優(yōu)點,但是不可避免的都是根據(jù)工作環(huán)境來設(shè)計葉片。在工作過程中,葉型在氣動力和離心力的共同作用下會產(chǎn)生變形,導(dǎo)致葉型發(fā)生偏差,與原始設(shè)計工作葉型不符,所以要對葉片進(jìn)行預(yù)變形設(shè)計分析,以保證風(fēng)扇葉片在實際運行的尺寸和原始設(shè)計的尺寸一致或者趨近一致。近些年,復(fù)合材料在航空發(fā)動機(jī)上的應(yīng)用是目前一個全新的研究方向。復(fù)合材料因其比強(qiáng)度大,比剛度高,疲勞性能好,可設(shè)計其內(nèi)部纖維的含量和內(nèi)部結(jié)構(gòu)的鋪設(shè)方式等優(yōu)秀條件,逐漸取代了原本金屬基材料的地位,成為航空發(fā)動機(jī)風(fēng)扇葉片的重要材料之一,因而研究復(fù)合材料風(fēng)扇葉片預(yù)變形設(shè)計具有重要的現(xiàn)實意義。本文綜合使用UG NX、Visual Studio2010、ANSYS、C/C++編程語言和APDL語言,完成葉片的參數(shù)化建模、復(fù)合材料工程彈性系數(shù)的設(shè)定以及預(yù)變形迭代算法的運行。具體研究內(nèi)容如下:(1)利用UG/Open API函數(shù)和Menuscript模塊,依靠C/C++編程語言的支持,在VS2010的編譯器中,完成了對復(fù)合材料風(fēng)扇葉片的參數(shù)化建模。從關(guān)鍵點的導(dǎo)入到葉片截面線的建立再到整體葉身的創(chuàng)建全部由程序代碼自動運行,實現(xiàn)了從點到線再到面的三維參數(shù)化建模,為后續(xù)的有限元分析奠定了基礎(chǔ)。(2)根據(jù)葉片的工作情況以及力學(xué)性能要求,采用各向異性復(fù)合材料(HT3/5224)作為風(fēng)扇葉片的材料,用ANSYS軟件完成葉片相關(guān)工程彈性系數(shù)的設(shè)定,應(yīng)用SOLID46單元在葉片模型中建立層合板結(jié)構(gòu),最后將氣動力和離心力加載到葉片模型上,完成變形分析。(3)使用APDL語言,提取原始葉型和變形之后的葉型之間的位移差值,采用反向疊加的方法進(jìn)行節(jié)點位移之間的迭代計算,疊加位移之后的模型和原始設(shè)計模型的最大位移差值在第1次迭代之后為0.1994mm,在15次迭代計算之后,最大位移差值的數(shù)量級已經(jīng)下降到10-8(mm)單位,結(jié)果表明,在10-6(mm)單位的時候,對于空間上節(jié)點坐標(biāo)來說已經(jīng)達(dá)到了收斂的條件,說明得到的預(yù)變形模型滿足設(shè)計要求。綜上所述,本文完成了復(fù)合材料風(fēng)扇葉片的參數(shù)化建模、相關(guān)復(fù)合材料工程彈性系數(shù)的設(shè)定、氣動離心載荷插值、迭代計算位移差值和預(yù)變形設(shè)計葉型。對復(fù)合材料風(fēng)扇葉片的設(shè)計有著一定的參考價值。
[Abstract]:Although there are many advantages in the traditional design method of aeroengine fan blade, it is inevitable to design the blade according to the working environment. In the working process, the blade shape will be deformed under the combined action of aerodynamic force and centrifugal force, which will lead to the deviation of the blade shape, which does not conform to the original design of the working blade shape, so the pre-deformation design analysis of the blade should be carried out. To ensure that the fan blade in the actual operation of the size and the original design of the same or close to the same. In recent years, the application of composite materials in aeroengine is a new research direction. Because of its high specific strength, high specific stiffness and good fatigue properties, composite materials can be designed for the content of internal fibers and the laying way of internal structures, gradually replacing the status of the original metal-based materials. As one of the most important materials for aero-engine fan blades, it is of great practical significance to study the pre-deformation design of composite fan blades. In this paper, using UG NXX Visual Studio 2010 C / C programming language and APDL language, the parametric modeling of blade, the setting of elastic coefficient of composite engineering and the operation of predeformation iterative algorithm are completed. The specific research contents are as follows: (1) using UG/Open API function and Menuscript module and supported by C / C programming language, the parameterized modeling of composite fan blade is completed in the compiler of VS2010. From the introduction of the key point to the establishment of the blade section line to the creation of the whole blade body, the program code runs automatically, which realizes the 3D parameterized modeling from point to line to plane. It lays the foundation for the subsequent finite element analysis. (2) according to the working condition of the blade and the requirement of the mechanical properties, the anisotropic composite material HT3 / 5224) is used as the material of the fan blade, and the elastic coefficient of the blade related engineering is set by ANSYS software. The laminated plate structure was built by SOLID46 element in the blade model. Finally, the aerodynamic force and centrifugal force were loaded into the blade model, and the deformation analysis was completed. Using APDL language, the displacement difference between the original leaf shape and the deformed leaf shape was extracted. The maximum displacement difference between the superposition model and the original design model is 0.1994mm after the first iteration, and after 15 iterations, the maximum displacement difference between the superposition model and the original design model is 0.94 mm after the first iteration. The order of magnitude of the maximum displacement difference has been reduced to 10-8 mm) units. The results show that the convergence condition has been reached for the coordinates of nodes in space at 10-6 mm) units, indicating that the pre-deformation model can meet the design requirements. To sum up, the parametric modeling of composite fan blade, the setting of elastic coefficient of composite material engineering, the interpolation of aerodynamic centrifugal load, the iterative calculation of displacement difference and the pre-deformation design of blade profile are completed in this paper. It has certain reference value for the design of composite fan blade.
【學(xué)位授予單位】：華僑大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2016
【分類號】：V232.4

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