Deformation and fatigue life analysis of axial flow compressor blade based on fluid-structure interaction
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Xinzhe Zhang
Abstract
This study employs the fluid-structure interaction (FSI) method to quantitatively evaluate the impact of different tip clearances on compressor blade performance, focusing on the influence of flow fields on structural behavior. The computational fluid dynamics (CFD) models utilized herein have been corroborated with experimental data. The vibration characteristics of blades were obtained based on the Campbell diagram, and fatigue life prediction was finally carried out. The results indicate that as the blade tip clearance increases from 0 times the design clearance to 2 times the design clearance, the tip vortex in blade tip flow field gradually strengthens, leading to a decrease in pressure ratio and efficiency, while the stable operating range of blade is shortened. Blade vibration modes are predominantly influenced by centrifugal loads, with tip clearance exerting a minor effect on these characteristics. The Campbell diagram indicates that the blade has low resonance margins at the design speed ranges of 54–59 % and 78–83 %, which are prone to resonance. After FSI calculations, it was found that the increase in blade tip clearance enhances the wing tip leakage vortex, reduces the aerodynamic load on blade, gradually reduces the maximum deformation of blade, and increases the fatigue life of blade.
Funding source: National Natural Science Foundation of China
Award Identifier / Grant number: 52206059
Funding source: Foundation of Henan Key Laboratory of General Aviation Technology
Award Identifier / Grant number: ZHKF-230202
Funding source: Key Scientific Research Projects of Colleges and Universities in Henan Province
Award Identifier / Grant number: 25A590002
Funding source: Graduate Education Innovation Foundation of Zhengzhou University of Aeronautics
Award Identifier / Grant number: 2024CX69
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Research ethics: Not applicable.
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Informed consent: Informed consent was obtained from all individuals included in this study or their legal guardians or wards.
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Author contributions: All authors have accepted responsibility for the entire content of this manuscript and approved its submission. The contributions of each author are as follows: Xinzhe Zhang: conceptualization, methodology, project administration, funding acquisition, formal analysis and editing. Bin Yu: methodology, formal analysis and editing, writing – original draft. Yuanyuan Jiang: formal analysis and editing. Guoju Li: writing – reviewing and editing, formal analysis.
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Use of Large Language Models, AI and Machine Learning Tools: None declared.
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Conflict of interest: The authors state no conflict of interest.
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Research funding: This research was funded by the National Natural Science Foundation of China (Grant No. 52206059); Foundation of Henan Key Laboratory of General Aviation Technology (Grant No. ZHKF-230202); Key Scientific Research Projects of Colleges and Universities in Henan Province (Grant No. 25A590002); and Graduate Education Innovation Foundation of Zhengzhou University of Aeronautics (Grant No. 2024CX69).
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Data availability: The data used for comparison in this study were obtained from previously published research articles, which are cited in the manuscript.
References
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© 2025 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- A novel degradation estimation of lifecycle health monitoring for aircraft engine gas path rotational components
- Minimum specific fuel consumption performance-seeking control for variable cycle engine based on CHOA-SQP hybrid algorithm and active disturbance rejection control
- Effects of splitter blade on vaned-diffuser stall and the corresponding warning method
- Uncertainty quantification of leakage characteristics of stepped labyrinth seals based on sparse PC-Kriging model
- Uncertainty propagation in transient heat transfer from an extended surface
- Impact of mass flow ratio on the aero-thermal performance of a film-cooled nozzle guide vane
- Quantification of uncertainty propagation in transient heat transfer from flux-base extended surface
- Recent advancements in Scramjet combustor: technologies, fuel strategies, and performance challenges
- Deformation and fatigue life analysis of axial flow compressor blade based on fluid-structure interaction
- Impact of convex-side blade attachments on savonius vertical axis wind turbines performance at low wind speeds
- An energy method for dry friction damping of ring damper in labyrinth seal structure under radial vibration
- Uncertainty quantification by probabilistic analysis of Stirling engine performance
- Integration of multi module flow domain to demonstrate the full engine aero-flow path simulation of Single Spool Turbojet Engine
- Enhancing fuel-air mixing and flame stability using double cavity with multiple struts scramjet propulsion
- Investigation on aerodynamic interference mechanism of a contra-rotating propfan under take-off condition
- Analysis of the dynamic characteristics of compliant foil gas seal with bearing-rotor system
- Investigation of the influence of an S-shaped isolator on the combustion characteristics of a supersonic combustion chamber
- Research on adjoint-based customized integrated passage design of Rotor 67
- A method for evaluating the time-averaged and unsteady characteristics of flow loss in axial compressors
Articles in the same Issue
- Frontmatter
- A novel degradation estimation of lifecycle health monitoring for aircraft engine gas path rotational components
- Minimum specific fuel consumption performance-seeking control for variable cycle engine based on CHOA-SQP hybrid algorithm and active disturbance rejection control
- Effects of splitter blade on vaned-diffuser stall and the corresponding warning method
- Uncertainty quantification of leakage characteristics of stepped labyrinth seals based on sparse PC-Kriging model
- Uncertainty propagation in transient heat transfer from an extended surface
- Impact of mass flow ratio on the aero-thermal performance of a film-cooled nozzle guide vane
- Quantification of uncertainty propagation in transient heat transfer from flux-base extended surface
- Recent advancements in Scramjet combustor: technologies, fuel strategies, and performance challenges
- Deformation and fatigue life analysis of axial flow compressor blade based on fluid-structure interaction
- Impact of convex-side blade attachments on savonius vertical axis wind turbines performance at low wind speeds
- An energy method for dry friction damping of ring damper in labyrinth seal structure under radial vibration
- Uncertainty quantification by probabilistic analysis of Stirling engine performance
- Integration of multi module flow domain to demonstrate the full engine aero-flow path simulation of Single Spool Turbojet Engine
- Enhancing fuel-air mixing and flame stability using double cavity with multiple struts scramjet propulsion
- Investigation on aerodynamic interference mechanism of a contra-rotating propfan under take-off condition
- Analysis of the dynamic characteristics of compliant foil gas seal with bearing-rotor system
- Investigation of the influence of an S-shaped isolator on the combustion characteristics of a supersonic combustion chamber
- Research on adjoint-based customized integrated passage design of Rotor 67
- A method for evaluating the time-averaged and unsteady characteristics of flow loss in axial compressors
