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首页> 外文期刊>Journal of Engineering for Gas Turbines and Power >Analysis of Composite Blade/ Casing Rub Stability Through Delayed Differential Equations
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Analysis of Composite Blade/ Casing Rub Stability Through Delayed Differential Equations

机译：用时滞微分方程分析复合叶片/机匣的摩擦稳定性。

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To improve aerodynamic efficiencies, the clearances between blades and casings are becoming smaller and smaller in the aero-engine industry, which might lead to the interactions between these components. These unexpected interactions are known as the so-called blade/casing rubs. Abradable materials are implemented on the inner surface of the casings to reduce the potential damages caused by it. However, failures may still arise from blade/casing rubs according to experimental investigations and actual accidents. In this paper, a reduced-order delayed differential equations (DDEs) are used to simplify the rubbing process between composite blade and casing. It is assumed that the removal of the abradable material in blade/casing rubbing process shares a resemblance with machine tool chatters encountered in machining. The DDEs are established with centrifugal stiffness and the impacts of stacking sequences on the blade damping taking into consideration. Semidiscretization method (SDM) is used to study the stabilities of the simplified system, which is verified by cluster treatment of characteristic roots (CTCR) and direct integrations. The results show that the stacking sequences, rub positions, blade damping, and stiffness could have much impact on the relatively dangerous interaction regimes. With the help of this method, one can assist the design processes of the composite blade-casing interface in initial aero-engine structural designs.
机译：为了提高空气动力学效率，在航空发动机工业中，叶片和壳体之间的间隙越来越小，这可能导致这些组件之间的相互作用。这些意外的相互作用被称为所谓的叶片/外壳摩擦。外壳的内表面采用可磨耗的材料，以减少由其引起的潜在损坏。但是，根据实验研究和实际事故，刀片/外壳磨擦仍可能导致故障。在本文中，使用降阶延迟微分方程（DDE）来简化复合材料叶片与壳体之间的摩擦过程。假定在刮刀/套管摩擦过程中去除可磨耗材料与在加工中遇到的机床颤振相似。建立DDE时要考虑离心刚度，并考虑堆叠顺序对叶片阻尼的影响。半离散化方法（SDM）用于研究简化系统的稳定性，该特征已通过特征根的聚类处理（CTCR）和直接积分得到了验证。结果表明，堆垛顺序，摩擦位置，叶片阻尼和刚度可能会对相对危险的相互作用方式产生很大影响。借助这种方法，可以在初始航空发动机结构设计中协助复合叶片-壳体接口的设计过程。

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    《Journal of Engineering for Gas Turbines and Power》 |2020年第1期|011009.1-011009.9|共9页
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    School of Mechanical Engineering Shanghai Jiao Tong University Shanghai 200240 China;

    School of Mechanical Engineering Shanghai Jiao Tong University Shanghai 200240 China Engineering Research Center of Gas Turbine and Civil Aero Engine Ministry of Education Shanghai 200240 China;

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