航空发动机双辐板涡轮盘温度场与应力场分析  

Analysis of temperature field and stress field for the twin-web turbine disk of aero engine

作　　者：金琰[1] 郝艳华[1] 黄致建[1] 

机构地区：[1]华侨大学机电及自动化学院,福建厦门361021

出　　处：《郑州轻工业学院学报（自然科学版）》2015年第1期81-84,共4页Journal of Zhengzhou University of Light Industry:Natural Science

摘　　要：基于ANSYS软件,研究了双辐板涡轮盘的温度场和应力场,通过划分各个区域的换热模型,较精确地计算了温度分布,再通过间接热-结构耦合计算出双辐板涡轮盘的应力分布.结果表明,双辐板涡轮盘最大平均径向应力、最大平均周向应力、盘心平均周向应力分别为702.35 MPa,679.68 MPa和880.98 MPa,不仅可满足规范设计要求的安全系数,还远小于材料的屈服强度1 070 MPa,其结构完全满足了强度要求,并具有很大的发展空间.The temperature field and stress field of the twin-web turbine were studied based on the ANSYS. Through dividing different parts of the turbine disk into different heat transfer model,the temperature field distribution was accurately calculated.And then the stress field distribution of the twin-web turbine disk was calculated by using the method of the indirect heat-structure coupling.The results showed that the maximum average radial stress,the maximum average circumferential stress and the average circumferential stress of plate heart were 702.35 MPa,679.68 MPa and 880.98 MPa,respectively.It not only met the re-quirement of the safety sactor,but also was less than the value of the yield strength,1 070 MPa.So the structure completely met the requirements of strength,and had the large development potential.

关 键 词：航空发动机 双辐板涡轮盘 换热边界 温度场 应力分布 

分 类 号：V232.3[航空宇航科学与技术—航空宇航推进理论与工程]