高压涡轮机匣典型结构热固耦合优化设计

发布时间：2018-07-22 17:07

【摘要】：发动机机匣设计中,主要依靠恰当的机匣结构和冷却流路设计来控制转子部件和机匣的径向位移,从而达到控制叶尖间隙的目的。机匣典型结构的优化设计是机匣结构设计中必不可少的一环。本文针对高压涡轮机匣轴对称模型热固耦合单目标以及多目标优化设计方法进行了研究,主包括以下三个方面的内容:(1)采用实验技术对高压涡轮机匣热固耦合分析方法进行验证,搭建相应试验台,获得模拟机匣热变形以及温度分布。针对实验工况下的模拟机匣进行热固耦合有限元分析,并对试验实测变形量和仿真变形量进行对比,结果表明:文中高压涡轮机匣热固耦合分析方法得到的温度及热变形精度基本符合工程应用要求。(2)建立基于UG表达式文件EXP驱动的高压涡轮机匣轴对称参数化模型,针对高压涡轮机匣轴对称参数化模型进行了热固耦合有限元分析,并对结构参数进行了灵敏度分析,基于灵敏度分析结果开展了高压涡轮机匣轴对称模型热固耦合单目标及多目标优化设计,优化结果表明:经过单目标优化之后,挂钩处径向平均位移值减小9.85%;经过多目标优化后机匣等效质量减轻4.54%,挂钩处径向平均位移值减小8.90%;跟单目标优化设计法相比,多目标优化设计更符合航空发动机设计需要。(3)采用响应面模型、人工神经网络模型以及Kriging模型构建了高压涡轮机匣热固耦合优化近似模型,对近似模型设置参数与预测精度之间关系进行研究,并利用近似模型对高压涡轮机匣模型进行了近似优化,结果表明:应用的三种近似模型均能够达到实际模型的优化效果,单目标优化选择基于径向基函数的人工神经网络模型(RBF),多目标优化选择总误差最小的响应面模型(RSM)。
[Abstract]:In the design of engine casing, the radial displacement of rotor parts and casing is mainly controlled by proper casing structure and cooling flow path design, so as to control the tip clearance. The optimal design of the typical casing structure is an indispensable part of the casing structure design. In this paper, the optimization design method of thermo-solid coupling and multi-objective optimization for axisymmetric model of high-pressure turbine casing is studied. The main contents include the following three aspects: (1) the thermal-solid coupling analysis method of high-pressure turbine casing is verified by experimental technology, and the corresponding test bench is built to obtain the simulation of heat deformation and temperature distribution of the casing. The thermo-solid coupling finite element analysis is carried out for the simulated casing under experimental conditions, and a comparison between the measured deformation and the simulated deformation is carried out. The results show that the temperature and thermal deformation accuracy obtained by the thermal-solid coupling analysis method of high pressure turbine casing basically meet the requirements of engineering application. (2) the axisymmetric parameterized model of high pressure turbine casing driven by UG expression file exp is established. Based on the axisymmetric parameterized model of high pressure turbine casing, the thermo-solid coupling finite element analysis is carried out, and the sensitivity analysis of structural parameters is carried out. Based on the sensitivity analysis results, the thermo-solid coupled single-objective and multi-objective optimization design of the axisymmetric model of high-pressure turbine casing is carried out. The optimization results show that: after single-objective optimization, After multi-objective optimization, the equivalent mass of the casing is reduced by 4.54 and the radial average displacement at the hook is reduced by 8.90. Compared with the single objective optimization design method, Multi-objective optimization design is more in line with the need of aeroengine design. (3) using response surface model, artificial neural network model and Kriging model, the thermo-solid coupling optimization approximation model of high-pressure turbine casing is constructed. The relationship between the parameters of the approximate model and the prediction accuracy is studied, and the high pressure turbine casing model is approximately optimized by using the approximate model. The results show that the three kinds of approximate models can achieve the optimization effect of the actual model. The radial basis function based artificial neural network model (RBF) and the response surface model (RSM) with minimum total error are selected for single objective optimization.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V231.1

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