GH536燃烧室帽罩粘性介质结合翻边成形应力场数值分析

Numerical Analysis of the Stress Field of GH536 Combustor Cap with Viscous Pressure Forming Combined with Flanging

针对航空发动机燃烧室帽罩成形难度大、易失稳起皱等问题,进行了粘性介质结合翻边成形有限元仿真研究,研究结果表明,帽罩中心开孔尺寸决定了环形凸起复杂曲面区域的应力场分布,在预成形过程中,环形凸起区域均由残余压应力与拉应力混合组成,增加开孔尺寸,环形凸起表面拉应力均值有下降的趋势,在二次成形过程中,受中心孔尺寸优化影响,残余拉应力与压应力均值及极值的分布均匀,帽罩环形凸起区域没有明显褶皱出现。在翻边成形过程中,采用2m/s凸模进给速度,模型整体成形应力均匀性提高,符合成形要求。

Aiming at the difficulty of forming the aero-engine combustor cap, easy instability and wrinkling,the finite element simulation study of viscous pressure combined with flanging forming is carried out. The research results show that the size of the hole in the center of the cap determines the stress field distribution in the complex surface area of the annular bulge. During the pre-forming process, the annular convex area is composed of a mixture of compressive residual stress and tensile stress. With the increase of the opening size, the average tensile stress on the annular convex surface tends to decrease.During the secondary forming process, affected by the optimization of the central hole size, the distribution of the mean and extreme values of tensile residual stress and compressive residual stress is uniform, and no obvious wrinkles appear in the annular convex area of the cap. In the flanging forming process, the punch feed speed of 2m/s is adopted, and the uniformity of the overall forming stress distribution of the model is improved, which meets the forming requirements.