This study examines the deformation and stress characteristics of an aerospace turbine wheel under centrifugal, thermal and pressure loads. Design modification is focused on the neck of the disk, which is a structurally critical area. Increasing the neck thickness significantly reduces radial deformation from centrifugal force, while thermal and pressure-induced deformations remain nearly unchanged. Stress at the blade root is minimally affected by geometric changes, but the disk neck stresses decrease notably when the radius is between 3.25 and 4.00 mm. Beyond 4.00 mm, stress rises again due to a shift in the peak stress location to the rear side. Yielding is first observed at a 3.5 mm radius, where deformation is also reduced to 0.29 mm. This geometry thus offers the best balance between strength and deformation. The findings provide a method to determine optimal neck design for prescribed design conditions.

The turbine wheel plays a crucial role in operating turbines, and with recent advancements in technology, the performance requirements for turbine wheels have significantly increased. Consequently, it is essential to predict failure speeds, as turbine wheels must maintain high stability and reliability under harsh operating conditions. In this study, only the centrifugal loads generated by rotati were considered, excluding conditions such as temperature and pressure. A round-shaped fuse section was applied to the turbine wheel, and the stresses induced by variations in shape were analyzed to predict failure speeds. The results obtained using the Hallinan criteria were compared with the results from finite element analysis (FEA) to validate the predicted failure speeds, showing good agreement between the two methods.