涡轮盘关键部位多圆弧设计及多变量优化

于洪飞; 赵巍; 付强; 王佰智

doi:10.13224/j.cnki.jasp.2017.12.005

涡轮盘关键部位多圆弧设计及多变量优化

doi: 10.13224/j.cnki.jasp.2017.12.005

1.
中国航空发动机集团有限公司中国航空发动机研究院，北京 101304
2.
中国航空发动机集团有限公司沈阳发动机研究所，沈阳 110015

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出版历程
- 收稿日期: 2016-05-12
- 刊出日期: 2017-12-28

Design of key part on turbine disk using multiarcs method and multivariable optimization

摘要

摘要: 为得到质量最低且满足设计准则要求的涡轮盘结构形式，研究了多圆弧过渡对涡轮盘关键部位应力的影响。提出了双圆弧和三圆弧结构设计方案并推导了几何关系，为过渡圆弧的改进与优化提供了理论上的支持。通过有限元计算，获得了多圆弧结构参数对涡轮盘应力的影响规律。基于ANSYS Workbench优化平台及参数化建模技术，筛选了优化设计变量，以涡轮盘总质量最小为优化目标，以等效应力为约束对涡轮盘关键部位进行了多变量优化。结果表明：经过优化设计，两个关键部位的最大应力分别降低662%和11.40%，涡轮盘的质量减小0.16%。本文的研究结果为涡轮盘的多圆弧设计和工程应用提供了有益参考。
- 涡轮盘 /
- 结构设计 /
- 多圆弧 /
- 影响规律 /
- 多变量优化
Abstract: In order to obtain the structure type of turbine disk satisfying minimum masses and stress standards, the influence of multiarcs transition on stress distribution at key parts was studied. Doublearcs and threearcs structure design schemes were proposed, and geometric theory on arcs transition was derived to support the design modifications and optimization. Based on finite element calculation, the stress varying with structure parameters was obtained. Based on ANSYS Workbench platform and parametric modeling technique, optimization design variables were chosen to get minimum masses with constrained equivalent stress. Result showed that, the maximum equivalent stress on two parts decreased by 662% and 1140%, the mass of turbine disk decreased by 016%. The results provide useful references for multiarcs design and engineering applications of the gas turbine disk.
- turbine disk /
- structure design /
- multiarcs /
- change law /
- multivariable optimization

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