本文關鍵詞：高速柔性轉(zhuǎn)子突加大不平衡響應研究　出處：《浙江大學》2014年碩士論文　論文類型：學位論文

  更多相關文章： 高速柔性轉(zhuǎn)子 葉片飛脫 突加不平衡響應 限位支承載荷 數(shù)值仿真 整體振動 響應試驗器

【摘要】：高速柔性轉(zhuǎn)子葉片飛脫后產(chǎn)生的突加大不平衡載荷對轉(zhuǎn)子以及安裝環(huán)節(jié)的結構振動響應是現(xiàn)代航空發(fā)動機研究領域關注的重點。通過模擬葉片飛脫試驗與數(shù)值仿真方法相結合,研究葉片飛脫后高速柔性轉(zhuǎn)子的突加不平衡響應特性。主要完成了以下工作： (1)建立了簡化的轉(zhuǎn)子-支承模型,利用LS-DYNA進行了葉片飛脫的模擬仿真計算。研究了不同飛脫質(zhì)量以及不同飛脫轉(zhuǎn)速下轉(zhuǎn)子的不平衡響應。通過仿真分析,深入研究了不同質(zhì)量和不同飛脫轉(zhuǎn)速下,轉(zhuǎn)子的不平衡響應以及限位支承處的受力,分析得到了轉(zhuǎn)子的失效形式為軸的扭斷失效,轉(zhuǎn)子在與限位支承發(fā)生碰磨時,表現(xiàn)為兩種狀態(tài)：一種是轉(zhuǎn)子與限位支承保持非連續(xù)的碰擦情況下,轉(zhuǎn)子不斷回彈減少不平衡響應,這種碰擦使得軸自身發(fā)生扭轉(zhuǎn)變形,此時的變形是可以恢復的；另外一種是轉(zhuǎn)子與限位支承持續(xù)碰擦而無回彈現(xiàn)象時,轉(zhuǎn)子的扭轉(zhuǎn)變形將使軸在最薄弱的地方發(fā)生扭斷。這兩種狀態(tài)在不平衡響應中順序發(fā)生。限位支承在不平衡響應中起到限位保護作用,研究表明隨著離限位支承的軸向距離的增加,這種限位保護作用越弱。對比了限位支承與軸系間隙分別為0.5mm、1mm、1.5mm三種情況下的不平衡響應,碰磨力隨著間隙的變化呈現(xiàn)先增加后減少的趨勢,但是間隙過大,限位支承不能很好起到限位保護的作用,可見碰磨力的大小并不能作為唯一反應軸系危險情況的指標,還需要綜合考慮轉(zhuǎn)子的軸心位移。 (2)利用ZUST6D型轉(zhuǎn)子高速旋轉(zhuǎn)試驗臺,研究葉片飛脫導致的突加不平衡載荷下高速柔性轉(zhuǎn)子的動力學響應。比較了不同飛脫葉片的重量和葉片飛脫形式對轉(zhuǎn)子軸系的突加不平衡響應的影響；發(fā)現(xiàn)單葉片飛脫與葉片順序飛脫相比,瞬時轉(zhuǎn)子振動與限位支承的承載所能達到的幅值具有相同的量級；但是單葉片飛脫對高速柔性轉(zhuǎn)子帶來的危害性更大,長時間的大不平衡量傳遞給限位支承-支承座-保護環(huán)-吊架,使支承-支承座-吊架系統(tǒng)產(chǎn)生了劇烈的振動響應,這種響應在真實發(fā)動機中可能導致安裝節(jié)失效；對于相同質(zhì)量的飛脫葉片,較高的飛脫轉(zhuǎn)速會導致限位支承-支承座-保護環(huán)-吊架系統(tǒng)更劇烈的振動響應；在相同的飛脫轉(zhuǎn)速下,較大的飛脫質(zhì)量會導致限位支承-支承座-保護環(huán)-吊架系統(tǒng)更劇烈的振動響應。 (3)設計了采用渦輪增壓器為主要部件的專用于葉片飛脫整體振動響應研究的臥式高速旋轉(zhuǎn)試驗器,并完成了試驗器的初步搭建和開機測試,提出了對試驗器的改進方案。
[Abstract]:High speed flexible rotor blade fly off produced after the sudden unbalance vibration load on the rotor and the installation part of response is the research focus of modern aero engine. Through simulation of blade flying test and numerical simulation method combining research on blade fly off after high speed flexible rotor sudden unbalance response characteristics. Complete the following work:
(1) establish a simplified rotor bearing model was analyzed by LS-DYNA simulation and calculation of the blades. Effects of different quality and different flying fly off speed rotor unbalance response. Through simulation analysis, in-depth study of the speed of different quality and different fly, rotor unbalance response and the limit support force, analysis of the failure forms of the rotor axis of the rotor in the broken failure, and limiting support rubbing, can be divided into two states: one is the rotor and limiting support to keep non continuous grazing conditions, continue to reduce springback rotor unbalance response. This scoop the shaft itself at the torsional deformation, deformation can be restored; the other is the rotor and limiting support continuous grazing and no rebound phenomenon, the rotor torsional deformation will make the shaft in the weakest place this break. Two states in the unbalance response sequence. Limiting support in unbalance limit protection effect to the response, the research shows that with the limit bearing axial distance increases, the limit protection effect is weak. Comparing the limit bearing and shafting clearance were 0.5mm, 1mm, unbalance response 1.5mm under three kinds of situations, rub impact force as the gap changes showed decreasing trend after the first increase, but the gap is too large, limiting support can play a good role in limiting protection, visible rubbing force and not as the only reaction shafting dangerous situation index, also need axis displacement of rotor comprehensive consideration.
(2) the use of ZUST6D type high-speed rotating rotor test rig, research on blade fly off caused by the sudden unbalance response of high speed flexible rotor dynamic load. The comparison of effects of different weight flies off the leaves and leaves fly off form of rotor shaft of the sudden unbalance response; found in leaf and leaf fly off order fly off compared to the amplitude of transient vibration of the rotor bearing and limiting support can be achieved by having the same order of magnitude; but the leaf fly off to bring harm to the high speed flexible rotor is larger, long time and large amount of unbalance is transferred to the limit bearing supporting seat - protection ring hanger, to support the supporting seat - suspension system produced severe vibration response, this response in a real engine installation may lead to joint failure; to fly off the same quality of blade, fly off speed will lead to the limit of supporting bearing protection ring - - hanging high The vibration response of the frame system is more severe. Under the same flight speed, the larger flying mass will lead to more severe vibration response of the limit bearing support seat protection ring hanger system.
(3) a horizontal high speed rotary tester with turbocharger as main part is designed, which is dedicated to the whole vibration response of blades. The test and preliminary test of the tester are completed, and the improvement plan for the tester is put forward.

【學位授予單位】：浙江大學
【學位級別】：碩士
【學位授予年份】：2014
【分類號】：TH133

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