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Turbine Disk 60° Sector: Cyclic Symmetry MPC, High-Temperature Creep & S-N Fatigue Life Prediction
60° cyclic sector of a high-temperature Ti-6Al-4V gas turbine rotor disk with dovetail slot solved via cylindrical multipoint constraint (MPC) transformation, Norton–Bailey secondary creep, and Basquin S-N fatigue evaluation.
Aero-engine and power-generation turbine disks undergo intense centrifugal and thermal loading over thousands of operating hours. Modeling a single periodic sector drastically reduces computational size while preserving full 3D stress fidelity. This case analyzes a 60° sector (1/6 of a bladed disk) in Ti-6Al-4V subjected to a 5,000 N blade root centrifugal pull, enforcing cyclic MPCs between periodic cutting faces while computing creep accumulation and S-N fatigue margin.
1. Geometry & FEA Mesh
- •3D B-Rep CAD model (`turbine_disk_sector.step`, 18 CAD faces, 110 × 95.26 × 25 mm).
- •937 TET4 elements, 356 nodes, 1,068 DOFs.
- •Titanium Ti-6Al-4V: E = 115 GPa, ν = 0.32, ρ = 4,500 kg/m³, yield strength σ_y = 830 MPa; Norton–Bailey parameters A = 1e-36, n = 5; Basquin fatigue curve σ_f = 1.2 GPa, b = -0.09.
2. Loads & Boundary Conditions
- •Inner shaft bore rigidly clamped (`fix surface number 42`, R = 24 mm).
- •Cyclic symmetry transformation connecting periodic boundary faces (`cyclic surface number 43 surface number 44 sectors=6 axis=0,0,1`).
- •Centrifugal radial blade pull of 5,000 N applied to dovetail upper contact land (`load surface number 34 force=5000 component=x`).
3. Simulation Results & Findings
- ✓Cyclic MPC constraints satisfy continuity across periodic boundaries with zero kinematic gap or tangential shear jump.
- ✓Peak von Mises stress localized in the dovetail fillet reaches σ_vm = 26.87 MPa with peak radial deflection |u|_max = 0.0333 mm.
- ✓Basquin S-N fatigue evaluation predicts endurance well beyond high-cycle limits (log₁₀(N_f) = 18.03 cycles, cumulative damage D = 9.32e-19).
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