航天推进技术研究院主办
[1]张鹏飞,贾少锋,许开富,等.多级涡轮气热耦合仿真性能及强度对比研究[J].火箭推进,2020,46(01):76-82.
ZHANG Pengfei,JIA Shaofeng,XU Kaifu,et al.Comparative study on performance and strength of multi-stage turbine with aero-thermal coupling simulation[J].Journal of Rocket Propulsion,2020,46(01):76-82.
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ZHANG Pengfei,JIA Shaofeng,XU Kaifu,et al.Comparative study on performance and strength of multi-stage turbine with aero-thermal coupling simulation[J].Journal of Rocket Propulsion,2020,46(01):76-82.
多级涡轮气热耦合仿真性能及强度对比研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
46
期数:
2020年01期
页码:
76-82
栏目:
研究与设计
出版日期:
2020-02-29
- Title:
- Comparative study on performance and strength of multi-stage turbine with aero-thermal coupling simulation
- Keywords:
- turbine disk; aero-thermal coupling; aerodynamic performance; structural strength; equivalent stress
- 分类号:
- V43文献标识码:A 文章编号:1672-9374(2020)01-0076-07
- 摘要:
- 航空航天发动机中,涡轮工作环境恶劣,承受流动传热耦合作用下强烈的热冲击,其结构强度问题十分突出。分别采用气动仿真和气热耦合仿真对某多级涡轮结构开展气动和强度性能仿真研究,提取相应的热边界条件进行涡轮盘结构强度有限元计算。结果表明:两种分析方法得到的涡轮气动性能十分接近,但涡轮盘表面的温度分布存在较大差异,计算得到的径向变形偏差达16%,等效应力偏差达50～100 MPa,气热耦合仿真结果更为可靠。
- Abstract:
- In aerospace engines, the working environment of the turbine is harsh andthe turbine bears strong thermal shock under the coupling effect of flow and heat transfer. Its structural strength problem is very serious. The aerodynamic and strength performance of a multi-stage turbine was studied with the aerodynamic simulation and aero-thermal coupling simulation, respectively. The thermal boundary conditions are extracted to perform the finite element simulation of the turbine disk. The results show that the aerodynamic performance of the turbine obtained by the two analysis methods is very close, but the temperature distribution on the surface of the turbine disk is quite different. The deviation of the calculated radial deformation reaches 16% and the equivalent stress deviation is up to 50～100 MPa. The results of the aero-thermal coupling simulation are more reliable.
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相似文献/References:
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disk die forging process[J].Journal of Rocket Propulsion,2009,35(01):44.
[2]张继桐,黄道琼,郭景录,等.由转速判断涡轮盘行波谐振[J].火箭推进,2005,31(03):14.
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[3]任众,朱东华,许开富.多场环境下涡轮盘的强度与振动安全性仿真优化研究[J].火箭推进,2016,42(06):36.
REN Zhong,ZHU Donghua,XU Kaifu.Multiphysics-based simulation and optimization on strength and vibration security of turbine disk[J].Journal of Rocket Propulsion,2016,42(01):36.
备注/Memo
收稿日期:2018-08-26; 修回日期:2019-05-12基金项目:国家863项目(2015AA7053026)作者简介:张鹏飞(1987—),男,博士,研究领域为液体火箭发动机涡轮泵设计
更新日期/Last Update:
2020-02-25