Contact Stress Analysis and Fatigue Life Prediction of a Turbine Fan Disc
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Liang Yang
Abstract
Fan discs are critical components of an aero engine. In this paper, contact stress and life prediction of a turbine fan disc were investigated. A simplified pin/disc model was conducted to simulate the practical working condition under applied loads using finite element (FE) analysis. This study is devoted to examining the effects of interface condition of pin/disc such as gap and coefficient upon the maximum stress. The FE model indicated that the maximum stress occurs at the top right corner in the second pin hole, and larger gap or friction coefficient has a significant effect on the maximum stress. In addition, FE analysis without considering friction is also conducted. The results show that the dangerous point is similar to the result which considers friction and the stress state is relatively larger than that of considering friction. Finally, based on FE analysis result, life prediction for the fan disc is conducted to combine the material S-N curve, mean stress effects and concentration stress factor obtained by means of FE method.
Funding statement: Funding: This research was supported by the National Natural Science Foundation of China under contract number 11272082.
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©2016 by De Gruyter
Articles in the same Issue
- Frontmatter
- Probabilistic Fatigue Life Prediction of Turbine Disc Considering Model Parameter Uncertainty
- Experimental Investigation of Reacting Flow Characteristics in a Dual-Mode Scramjet Combustor
- Adjoint Optimization of Multistage Axial Compressor Blades with Static Pressure Constraint at Blade Row Interface
- Wall Pressure Measurements in a Convergent–Divergent Nozzle with Varying Inlet Asymmetry
- Thermoelastic Simulations Based on Discontinuous Galerkin Methods: Formulation and Application in Gas Turbines
- Re-Educating Jet-Engine-Researchers to Stay Relevant
- Analysis of a Turbine Blade Failure in a Military Turbojet Engine
- Investigation of Positively Curved Blade in Compressor Cascade Based on Transition Model
- Design and Experimentation of Simulated Combustor Model for Aircraft Afterburner Applications
- Contact Stress Analysis and Fatigue Life Prediction of a Turbine Fan Disc
- Multidisciplinary Design Optimization on Conceptual Design of Aero-engine
Articles in the same Issue
- Frontmatter
- Probabilistic Fatigue Life Prediction of Turbine Disc Considering Model Parameter Uncertainty
- Experimental Investigation of Reacting Flow Characteristics in a Dual-Mode Scramjet Combustor
- Adjoint Optimization of Multistage Axial Compressor Blades with Static Pressure Constraint at Blade Row Interface
- Wall Pressure Measurements in a Convergent–Divergent Nozzle with Varying Inlet Asymmetry
- Thermoelastic Simulations Based on Discontinuous Galerkin Methods: Formulation and Application in Gas Turbines
- Re-Educating Jet-Engine-Researchers to Stay Relevant
- Analysis of a Turbine Blade Failure in a Military Turbojet Engine
- Investigation of Positively Curved Blade in Compressor Cascade Based on Transition Model
- Design and Experimentation of Simulated Combustor Model for Aircraft Afterburner Applications
- Contact Stress Analysis and Fatigue Life Prediction of a Turbine Fan Disc
- Multidisciplinary Design Optimization on Conceptual Design of Aero-engine
