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.

Abstract
1. 서 론
2. 터빈 휠의 구조해석
    2.1 유한요소 모 델
    2.2 재질 특성
    2.3 유한요소 해석결과
3. 결 론
References

• 최복록(Professor, Gangneung- Wonju National University School of Mechanical & Automotive Engineering) | B. L. CHOI Corresponding author