本文選題：平板葉片 + 流固耦合��； 參考：《南京航空航天大學(xué)》2012年碩士論文

【摘要】：在葉輪機(jī)械中,引起葉片振動(dòng)的因素很多。其中作用在葉片上的流體擾動(dòng)力是激發(fā)振動(dòng)的最重要因素。 在葉片振動(dòng)過程中,一般通過分析坎貝爾圖來預(yù)測(cè)葉片工作時(shí)的共振狀態(tài),但是在航空發(fā)動(dòng)機(jī)工作范圍內(nèi)僅僅依靠坎貝爾圖中的幾個(gè)共振點(diǎn)來判斷發(fā)動(dòng)機(jī)工作中出現(xiàn)的危險(xiǎn)狀況及共振現(xiàn)象是遠(yuǎn)遠(yuǎn)不夠的,在共振點(diǎn)外的工作區(qū)域,發(fā)動(dòng)機(jī)葉片仍會(huì)有振動(dòng)現(xiàn)象,因此只能通過分析作用于葉片致使其產(chǎn)生振動(dòng)的氣體激振力才是最有效的方法,直接求解并控制葉片的振動(dòng)響應(yīng)(位移和應(yīng)力),從而分析造成葉片破壞的因素。 葉片周圍存在著氣體,而這些氣體力的分布情況決定著葉片振動(dòng)時(shí)的速度、位移的變化規(guī)律,然而葉片振動(dòng)過程中又會(huì)影響到葉片周圍氣體力的分布,促使流場(chǎng)中的結(jié)構(gòu)體發(fā)生形變。因此必須把氣體和結(jié)構(gòu)體兩個(gè)相互影響因素考慮進(jìn)去,才能準(zhǔn)確把握葉片真實(shí)振動(dòng)的細(xì)節(jié)問題。 本文在總結(jié)氣彈動(dòng)力學(xué)研究方法的基礎(chǔ)上,重點(diǎn)研究了基于多步流固耦合下氣體激振力預(yù)測(cè)方法及以Workbench/CFX為仿真工具,運(yùn)用多步耦合的方法對(duì)平板葉片進(jìn)行了振動(dòng)響應(yīng)分析。主要具體工作內(nèi)容如下： 1)提出了一種流固耦合下葉片氣體激振力預(yù)測(cè)方法。以平板葉片為研究對(duì)象,對(duì)有靜子平板葉片時(shí)的轉(zhuǎn)子平板葉片、無靜子平板葉片時(shí)的轉(zhuǎn)子平板葉片以及其周圍的流體域進(jìn)行建模,來模擬尾流激振的情況,利用Workbench和CFX仿真計(jì)算軟件,進(jìn)行流固耦合的數(shù)值模擬計(jì)算,得到平板葉片表面氣動(dòng)力收斂情況下的值,根據(jù)所得氣動(dòng)力值與葉片形變的關(guān)系建立最終穩(wěn)定時(shí)尾流激振下激振力的表達(dá)式。 2)在建立最終尾流激振力表達(dá)式的基礎(chǔ)上,研究了流固耦合下葉片強(qiáng)迫振動(dòng)分析方法,并對(duì)考慮流固耦合與不考慮流固耦合下轉(zhuǎn)子平板葉片的的強(qiáng)迫振動(dòng)響應(yīng)計(jì)算結(jié)果進(jìn)行對(duì)比與分析。 3)調(diào)整靜子葉片前的進(jìn)氣角,對(duì)流固耦合下轉(zhuǎn)子平板葉片進(jìn)行了諧響應(yīng)分析,獲得了在不同進(jìn)氣角下平板葉片振動(dòng)響應(yīng)的變化規(guī)律。 4)在上述研究的基礎(chǔ)上,分析了流固耦合下靜子葉片進(jìn)氣角對(duì)轉(zhuǎn)子葉片動(dòng)力穩(wěn)定性的影響。
[Abstract]:In impeller machinery, there are many factors causing blade vibration. The fluid disturbance force acting on the blade is the most important factor to excite vibration. In the process of blade vibration, the resonance state of blade is usually predicted by analyzing Campbell diagram. However, it is far from enough to judge the dangerous condition and resonance phenomenon in the work of the aeroengine only by several common vibration points in Campbell diagram, and the working area outside the common vibration point is far from enough. There is still vibration in the blade of the engine, so the most effective method is to analyze the gas excitation force that causes the blade to vibrate. The vibration response (displacement and stress) of the blade is directly solved and controlled, and the factors causing the blade failure are analyzed. There are gases around the blade, and the distribution of these gas forces determines the speed and displacement of the blade vibration, but the blade vibration process will affect the distribution of the gas force around the blade. Causes the structure in the flow field to deform. Therefore, gas and structure must be taken into account in order to accurately grasp the details of the real vibration of the blade. On the basis of summarizing the research methods of aero-elastic dynamics, this paper focuses on the prediction method of gas excitation force based on multi-step fluid-solid coupling and the vibration response analysis of flat plate blade using Workbench/CFX as simulation tool. The main contents of the work are as follows: 1) A prediction method of blade gas excitation force under fluid-solid coupling is proposed. Taking flat blade as research object, the rotor plate blade with stator blade, rotor plate blade with no stator blade and its surrounding fluid domain are modeled to simulate the wake induced vibration. By using Workbench and CFX software, the numerical simulation of fluid-solid coupling is carried out, and the results of aerodynamic convergence on the surface of flat blade are obtained. According to the relationship between the aerodynamic value and blade deformation, the expression of the induced force under the wake excitation is established. 2) based on the final expression of wake excitation force, the analysis method of blade forced vibration under fluid-solid coupling is studied. The calculation results of forced vibration response of rotor plate blade considering fluid-solid coupling and non-fluid-solid coupling are compared and analyzed. 3) by adjusting the inlet angle of the stator blade, the harmonic response of the rotor plate blade is analyzed under convection-solid coupling, and the variation law of the plate blade vibration response under different inlet angles is obtained. 4) on the basis of the above research, the influence of inlet angle of stator blade on the dynamic stability of rotor blade under fluid-solid coupling is analyzed.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2012
【分類號(hào)】：TH113.1

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本文編號(hào)：1863995