摘要
利用大型通用结构分析程序ＡＰＯＬＡＮＳ对某型航空发动机高压涡轮盘与叶片进行了热弹塑性蠕变接触分析，并与轮盘热弹塑性蠕变分析结果进行了比较，得出了一些有益的结论，为涡轮盘、叶片的应力应变分析提供了一种较为准确的方法。
A reliable method of contact analysis is presented for turbine disk with blades. As the temperatures of the turbine disk and the blade vary greatly,Oak Ridge Nat ional Laboratory′s creep law,in which th e effect of temperature on creep strain is considered,is applied and integrated into the general purpose structure analy sis program APOLANS.Then the thermal ela sto plastic creep contact analysis of a given turbine disk with blades has been carried out.The results show that the ef fective streeses and creep strains are s mall in most of zones,but a high stress zone appears in No.5 throat of disk.The peaks of the effective plastic and creep strain are 0.0164% and 0.01147% respect ively.The results of contact analysis we re compared with the ones of the thermal elasto plastic creep analysis of the di sk without contact.The comparision shows that there are different stress distrib utions near the contact zones.In the No. 5 throat of disk,where stress concentrat ion is most serious,the effective stress ,plastic strain,creep strain obtained by noncontact analysis are smaller than th ose obtained by the contact analysis.The refore it is unsafe to use the results o f noncontact analysis for strength check and life prediction.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
1995年第1期9-12,共4页
Journal of Aerospace Power
基金
航空科研基金
