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Creep-Based Reliability Evaluation of Turbine Blade-Tip Clearance with Novel Neural Network Regression

机译:新型神经网络回归的基于蠕变的涡轮叶片叶尖间隙可靠性评估

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摘要

To reveal the effect of high-temperature creep on the blade-tip radial running clearance of aeroengine high-pressure turbines, a distributed collaborative generalized regression extremum neural network is proposed by absorbing the heuristic thoughts of distributed collaborative response surface method and the generalized extremum neural network, in order to improve the reliability analysis of blade-tip clearance with creep behavior in terms of modeling precision and simulation efficiency. In this method, the generalized extremum neural network was used to handle the transients by simplifying the response process as one extremum and to address the strong nonlinearity by means of its nonlinear mapping ability. The distributed collaborative response surface method was applied to handle multi-object multi-discipline analysis, by decomposing one “big” model with hyperparameters and high nonlinearity into a series of “small” sub-models with few parameters and low nonlinearity. Based on the developed method, the blade-tip clearance reliability analysis of an aeroengine high-pressure turbine was performed subject to the creep behaviors of structural materials, by considering the randomness of influencing parameters such as gas temperature, rotational speed, material parameters, convective heat transfer coefficient, and so forth. It was found that the reliability degree of the clearance is 0.9909 when the allowable value is 2.2 mm, and the creep deformation of the clearance presents a normal distribution with a mean of 1.9829 mm and a standard deviation of 0.07539 mm. Based on a comparison of the methods, it is demonstrated that the proposed method requires a computing time of 1.201 s and has a computational accuracy of 99.929% over 10 simulations, which are improvements of 70.5% and 1.23%, respectively, relative to the distributed collaborative response surface method. Meanwhile, the high efficiency and high precision of the presented approach become more obvious with the increasing simulations. The efforts of this study provide a promising approach to improve the dynamic reliability analysis of complex structures.
机译:为了揭示高温蠕变对航空发动机高压涡轮叶片尖端径向游隙的影响,通过吸收分布式协同响应面法和广义极值神经的启发式思想,提出了一种分布式协同广义回归极值神经网络。网络,以提高在建模精度和仿真效率方面具有蠕变行为的叶尖间隙的可靠性分析。在这种方法中,广义极值神经网络用于简化瞬态响应过程,将其简化为一个极值,并利用其非线性映射能力解决了强烈的非线性问题。通过将一个具有超参数和高非线性的“大”模型分解为一系列参数少,非线性低的“小”子模型,将分布式协作响应表面方法应用于多对象多学科分析。在此基础上,结合气体温度,转速,材料参数,对流等影响参数的随机性,对航空发动机高压涡轮叶片进行了结构材料蠕变行为的叶尖间隙可靠性分析。传热系数,等等。发现,当允许值为2.2mm时,间隙的可靠度为0.9909,并且间隙的蠕变变形呈正态分布,其平均值为1.9829mm,标准偏差为0.07539mm。通过对方法的比较,表明所提出的方法需要10.201 s的计算时间,并且在10个仿真中的计算精度为99.929%,相对于分布式方法分别提高了70.5%和1.23%。协同响应面法。同时,随着仿真的增加,所提出的方法的高效率和高精度变得更加明显。这项研究的努力为改善复杂结构的动态可靠性分析提供了一种有前途的方法。

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