多级涡轮气热耦合仿真性能及强度对比研究  

Comparative study on performance and strength of multi-stage turbine with aero-thermal coupling simulation

作　　者：张鹏飞 贾少锋 许开富[1] 朱东华[1] 任众[1] ZHANG Pengfei;JIA Shaofeng;XU Kaifu;ZHU Donghua;REN Zhong(Xi'an Aerospace Propulsion Institute,Xi'an 710100,China)

机构地区：[1]西安航天动力研究所

出　　处：《火箭推进》2020年第1期76-82,共7页Journal of Rocket Propulsion

基　　金：国家863项目(2015AA7053026)

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。In aerospace engines,the working environment of the turbine is harsh and the 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.

关 键 词：涡轮盘 气热耦合 气动性能 结构强度 等效应力 

分 类 号：V43[航空宇航科学与技术—航空宇航推进理论与工程]