航空发动机燃烧室帽罩粘性介质成形数值仿真分析  

Numerical simulation analysis of viscous medium forming process for aero-engine combustion chamber cap

作　　者：李威[1] 石佩钰 陈淳 王朔[1] LI Wei;SHI Peiyu;CHEN Chun;WANG Shuo(College of Aerospace Engineering,Shenyang Aerospace University,Shenyang 110136,Liaoning China;AECC Xi'an Aero-Engine Co.,Ltd.,Xi'an 710021,Shaanxi China)

机构地区：[1]沈阳航空航天大学航空宇航学院,辽宁沈阳110136 [2]中国航发西安航空发动机有限公司,陕西西安710021

出　　处：《锻压装备与制造技术》2022年第4期119-122,共4页China Metalforming Equipment & Manufacturing Technology

基　　金：中国航发产学研合作项目(HFZL2019CXY024-1)。

摘　　要：针对航空发动机燃烧室帽罩成形质量难以精确控制等问题,进行了粘性介质成形工艺数值分析,根据压边间隙及成形压力的不同,建立了9组粘性介质成形有限元模型。结果显示,选定参数范围内,最大减薄率与增厚率均低于20%,与成形压力相比,压边间隙对环形凸起区域褶皱分布影响较小,提高成形压力,可有效避免成形区域褶皱的产生。结合环形凸起区域的褶皱分布情况,考虑到高减薄率带来的破裂等风险,最终选择压边间隙为1.26mm,成形压力为80MPa。Aiming at the problem that the forming quality of the aero-engine combustion chamber cap is difficult to control accurately, numerical analysis of the forming process of viscous medium has been carried out.Within the selected parameter range, the maximum thinning rate and thickening rate are both lower than 20%.Compared with the forming pressure, the blank holder gap has less influence on the wrinkle distribution in the annular raised area. Increasing the forming pressure can effectively avoid wrinkles in the forming area. In combination with the wrinkle distribution in the annular raised area, by considering the risk of rupture caused by the high thinning rate, the final selection of the blank holder gap is 1.26mm, while the forming pressure is 80MPa.

关 键 词：粘性介质成形 有限元 航空发动机 褶皱 成形压力 

分 类 号：V261.2[航空宇航科学与技术—航空宇航制造工程]