航空发动机初步设计阶段涡轮流道多学科优化设计分析方法

申秀丽; 龙丹; 董晓琳

doi:10.13224/j.cnki.jasp.2014.06.016

航空发动机初步设计阶段涡轮流道多学科优化设计分析方法

doi: 10.13224/j.cnki.jasp.2014.06.016

1. 北京航空航天大学能源与动力工程学院, 北京 100191;
2. 先进航空发动机协同创新中心, 北京 100191;
3. 中国运载火箭技术研究院研究发展中心, 北京 100191

详细信息

作者简介:
申秀丽（1967- ），女，山西襄垣人，研究员，硕士，主要从事航空发动机涡轮部件结构强度研究.

中图分类号: V231
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出版历程
- 收稿日期: 2013-04-04
- 刊出日期: 2014-06-28

Multidisciplinary design optimization of aero-engine turbine flow path in preliminary design phase

1. School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
2. Co-Innovation Center for Advanced Aero-Engine, Beijing 100191, China;
3. Research and Development Center, China Academy of Launch Vehicle Technology, Beijing 100191, China

摘要

摘要: 针对航空发动机涡轮初步设计阶段，在完成气动流道初步设计的前提下，综合考虑气动流道与叶片轮盘关键结构特征的制约和平衡关系，建立了关于高压涡轮气动流道和转子强度分析的多学科优化模型，进行了以气动流道效率和转子结构质量为目标函数的涡轮流道多学科多目标优化，优化后涡轮转子最大径向应力和最大周向应力分别下降4.62%和10.63%，同时危险截面处的平均径向应力和周向应力也分别下降了42.99%和3%，使涡轮部件气动和结构强度的多学科综合性能提高3.41%.
- 航空发动机总体设计 /
- 初步设计阶段 /
- 气动流道设计 /
- 转子强度计算 /
- 多学科设计优化
Abstract: In the preliminary design phase of aero-engine turbine, the turbine flow path was designed. The complex constraining and balanced relations between aerodynamic performance and turbine blade and disc strength were synthetically analyzed to establish turbine multidisciplinary optimization system of flow path design and turbine strength calculation, and to achieve the multidisciplinary design optimization of turbine flow path, with efficiency and structural weight as design targets. The maximum value of radial stress and circumferential stress are respectively decreased by 4.62% and 10.63%,the mean value of radial stress and circumferential stress in dangerous area are also decreased by 42.99% and 3%,and the turbine comprehensive performance in aerodynamic and structural strength are improved by 3.41% after optimization.
- aero-engine overall design /
- preliminary design phase /
- flow path design /
- turbine strength analysis /
- multidisciplinary design optimization

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参考文献(16)

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