Spiderweb inspired SiC/SiC composite aero-engine integrated turbine rotor and its multi-scale simulation

In order to improve the mechanical performance of SiC/SiC composite turbine discs, a spiderweb inspired integrated structure is developed in this work, which is achieved through polar braiding technology. Parallel to this, a four-level multi-scale (nano, micro, meso, and macro) modeling method is developed to simulate the mechanical properties of SiC/SiC composite integrated turbine disks. Among them, the molecular dynamics (MD) model of SiC/BN interface and the finite element (FE) model of trapezoidal cross-sectional braided RVE are innovative. Finally, experimental tests are conducted on the turbine disk, and the results showed that the invented turbine disk can achieve a rupture rotational speed of 10⁵ rpm and an expected service temperature of 1350 °C. The multi-scale numerical simulation method controlled the simulation error of the natural frequency of the turbine disk within 6 %. The results and conclusions of this work could provide new perspectives and insights into the application of SiC/SiC composites in advanced aero-engine rotor components.