高速柔性转子突加大不平衡响应研究

发布时间：2018-01-09 19:24

本文关键词：高速柔性转子突加大不平衡响应研究　出处：《浙江大学》2014年硕士论文　论文类型：学位论文

【摘要】：高速柔性转子叶片飞脱后产生的突加大不平衡载荷对转子以及安装环节的结构振动响应是现代航空发动机研究领域关注的重点。通过模拟叶片飞脱试验与数值仿真方法相结合,研究叶片飞脱后高速柔性转子的突加不平衡响应特性。主要完成了以下工作： (1)建立了简化的转子-支承模型,利用LS-DYNA进行了叶片飞脱的模拟仿真计算。研究了不同飞脱质量以及不同飞脱转速下转子的不平衡响应。通过仿真分析,深入研究了不同质量和不同飞脱转速下,转子的不平衡响应以及限位支承处的受力,分析得到了转子的失效形式为轴的扭断失效,转子在与限位支承发生碰磨时,表现为两种状态：一种是转子与限位支承保持非连续的碰擦情况下,转子不断回弹减少不平衡响应,这种碰擦使得轴自身发生扭转变形,此时的变形是可以恢复的；另外一种是转子与限位支承持续碰擦而无回弹现象时,转子的扭转变形将使轴在最薄弱的地方发生扭断。这两种状态在不平衡响应中顺序发生。限位支承在不平衡响应中起到限位保护作用,研究表明随着离限位支承的轴向距离的增加,这种限位保护作用越弱。对比了限位支承与轴系间隙分别为0.5mm、1mm、1.5mm三种情况下的不平衡响应,碰磨力随着间隙的变化呈现先增加后减少的趋势,但是间隙过大,限位支承不能很好起到限位保护的作用,可见碰磨力的大小并不能作为唯一反应轴系危险情况的指标,还需要综合考虑转子的轴心位移。 (2)利用ZUST6D型转子高速旋转试验台,研究叶片飞脱导致的突加不平衡载荷下高速柔性转子的动力学响应。比较了不同飞脱叶片的重量和叶片飞脱形式对转子轴系的突加不平衡响应的影响；发现单叶片飞脱与叶片顺序飞脱相比,瞬时转子振动与限位支承的承载所能达到的幅值具有相同的量级；但是单叶片飞脱对高速柔性转子带来的危害性更大,长时间的大不平衡量传递给限位支承-支承座-保护环-吊架,使支承-支承座-吊架系统产生了剧烈的振动响应,这种响应在真实发动机中可能导致安装节失效；对于相同质量的飞脱叶片,较高的飞脱转速会导致限位支承-支承座-保护环-吊架系统更剧烈的振动响应；在相同的飞脱转速下,较大的飞脱质量会导致限位支承-支承座-保护环-吊架系统更剧烈的振动响应。 (3)设计了采用涡轮增压器为主要部件的专用于叶片飞脱整体振动响应研究的卧式高速旋转试验器,并完成了试验器的初步搭建和开机测试,提出了对试验器的改进方案。
[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.

【学位授予单位】：浙江大学
【学位级别】：硕士
【学位授予年份】：2014
【分类号】：TH133

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