Strength and Vibration Analysis of Axial Flow Compressor Blades Based on the CFD-CSD Coupling Method
Abstract
:1. Introduction
2. Computational Methods
2.1. Flow Field Solution Method
2.2. Structural Solution Method
2.3. Data Transfer Method
3. Meshing and Computational Method Validation
3.1. Research Objectives
3.2. Boundary Conditions for the Fluid Domain
3.3. Boundary Conditions for the Structural Domain
3.4. Meshing
3.5. Method Validation
4. Results and Discussion
4.1. Influence of Different Loads on Blade Stress and Strain
4.2. Analysis of Blade Vibration Characteristics under Different Pre-Stresses
5. Conclusions
- (1)
- The deformation of the blades gradually increased along the blade height, with maximum deformation occurring at the lead edge tip. Regions of high stress were primarily concentrated at the upper 33% of the blade root, then radiated radially outward and gradually decreased. Both aerodynamic and centrifugal loads affected the magnitude and distribution of blade deformation and stress, but the influence of centrifugal loads on blade stress was significantly greater than that of aerodynamic loads, making centrifugal loads the primary consideration in stress calculations.
- (2)
- With increasing rotational speed, the maximum deformation of the blades showed a trend of initially increasing and subsequently decreasing, with maximum deformation under near-stall conditions exceeding that at near-choke points. However, the maximum stress of the blades exhibited a trend of initially increasing, subsequently decreasing, and then increasing, suggesting that selecting an appropriate rotational speed can reduce both the maximum deformation and maximum stress of the blades.
- (3)
- The natural frequencies of the blades increased with increasing rotational speed. Both centrifugal and aerodynamic loads had some degree of influence on the natural frequencies of the blades, but centrifugal loads were the primary factor affecting blade natural frequencies.
- (4)
- There were resonance points for compressor blades around 62% and 98% of the rotational speed. Care should be taken during compressor operation to prevent resonance, which could lead to blade damage.
Author Contributions
Funding
Institutional Review Board Statement
Informed Consent Statement
Data Availability Statement
Acknowledgments
Conflicts of Interest
References
- Chen, G. Structural Design and Analysis of Aerospace Engines, 3rd ed.; Beijing University of Aeronautics and Astronautics Press: Beijing, China, 2014. [Google Scholar]
- Jin, X.-M.; Gao, D.-P.; Cai, X.-X. Analysis of integrated centrifugal impeller blade vibration reliability. J. Aerosp. Power 2004, 19, 610–613. [Google Scholar]
- Ramamurti, V.; Subramani, D.A.; Sridhara, K. Free vibration analysis of a turbocharger centrifugal compressor impeller. Mech. Mach. Theory 1995, 30, 619–628. [Google Scholar] [CrossRef]
- Day, W.-D.; Fiebiger, S.W.; Patel, H.N. Parametric evaluation of compressor blade blending. Proc. ASME Turbo Expo 2012, 7, 1099–1110. [Google Scholar]
- Li, L.; Xu, P.; Xu, W.-X. Multi-field coupling vibration patterns of the multiphase sink vortex and distortion recognition method. Mech. Syst. Signal Process. 2024, 29, 111624. [Google Scholar] [CrossRef]
- Tan, Y.-F.; Ni, Y.-S.; Xu, W.-X. Key technologies and development trends of the soft abrasive flow finishing method. J. Zhejiang Univ. Sci. A 2023, 24, 1043–1064. [Google Scholar] [CrossRef]
- Tao, H.-L.; Zhu, Y.-L.; Guo, B.-T. Numerical simulation of aeroelastic response in compressor based on fluid-structure coupling. J. Aerosp. Power 2012, 27, 1054–1060. [Google Scholar]
- Tao, P. Analysis on compressor blade structure based on fluid-solid coupling. Des. Manuf. Diesel Engine 2014, 20, 8–11. [Google Scholar]
- Wang, D.-B.; Han, L.-L.; Wang, G.-H. The flow simulation in the compressor with the effect of fluid-solid interaction. J. Therm. Sci. Technol. 2020, 19, 64–71. [Google Scholar]
- Li, X. The Flow Simulation in the Compressor with the Effect of Fluid-Solid Interaction. Master’s Thesis, Harbin Institute of Technology, Harbin, China, 2010. [Google Scholar]
- Zhang, J.-H.; Fu, X.; Kou, H.-J. Numerical study on vibration characteristics of axial flow compressor blade under fluid-structure interaction. J. Therm. Sci. Technol. 2018, 38, 59–66. [Google Scholar]
- Li, C.-W.; Wang, C.; Li, Q. Modal analysis of aero-engine blade based on thermal-structure coupling pre-stressing force. J. Air Force Eng. Univ. (Nat. Sci. Ed.) 2016, 17, 1–4. [Google Scholar]
- Li, S. Preliminary Study on Axial Flow Fan Design Based on FLUENT Software. Master’s Thesis, Northwestern Polytechnical University, Xi’an, China, 2004. [Google Scholar]
- Guo, T.-Q.; Lu, Z.-L.; Zhou, D. Coupled CFD/CSD Calculation of Aircraft Aeroelasticity, 1st ed.; Science Press: Beijing, China, 2019. [Google Scholar]
- Reid, L.; Moore, R.D. Design and Overall Performance of Four Highly Loaded, High-Speed Inlet Stages for An Advanced High-Pressure-Ratio Core Compressor. NASA TP-1337. 1978. Available online: https://ntrs.nasa.gov/citations/19780025165 (accessed on 20 July 2024).
- Denton, J.D. Lessons from rotor 37. J. Therm. Sci. 1997, 6, 1–13. [Google Scholar] [CrossRef]
- Wang, W.; Chu, W.-L.; Zhang, H.-G. The effects on stability, performance, and tip leakage flow of recirculating casing treatment in a subsonic axial flow compressor. In Proceedings of the ASME Turbo Expo, Seoul, Republic of Korea, 13–17 June 2016. [Google Scholar]
- Wang, H. Study of Unsteady Tip Flow and Rotating Instability in Axial Compressors. Ph.D. Thesis, Shanghai Jiao Tong University, Shanghai, China, 2016. [Google Scholar]
- Boretti, A. Experimental and computational analysis of a transonic compressor rotor. Mar. Geol. 2010, 122, 243–262. [Google Scholar]
- Liu, Y.; Yang, C.; Ma, C.-C. Forced Responses on a Radial Turbine with Nozzle Guide Vanes. J. Therm. Sci. 2014, 23, 138–144. [Google Scholar] [CrossRef]
- Zhang, H.; Wang, X.-Y.; Zhang, Y.-F. Vibration Failure Characteristic Analysis of Compressor Impeller Under Plateau Conditions. Chin. Intern. Combust. Engine Eng. 2024, 45, 47–56. [Google Scholar]
Parameter | |
---|---|
Number of blades | 36 |
Tip clearance/mm | 0.356 |
Pressure ratio | 2.106 |
Adiabatic efficiency | 0.877 |
Inlet blade tip relative to Mach | 1.48 |
Inlet blade root relative Mach | 1.13 |
Design rotational speed/(rpm) | 17,188.7 |
Design flow rate/(Kg/s) | 20.19 |
Order | Mode | Load | Frequency (Hz) | |||
---|---|---|---|---|---|---|
Design Rotational Speed of 70% | Design Rotational Speed of 80% | Design Rotational Speed of 90% | Design Rotational Speed of 100% | |||
1 | First-order bending | Aerodynamic load | 927.48 | 927.98 | 928.58 | 929.01 |
Centrifugal load | 1050.9 | 1086 | 1124.2 | 1165.4 | ||
Centrifugal and Aerodynamic load | 1051.6 | 1086.8 | 1125.3 | 1166.5 | ||
2 | First-order torsion | Aerodynamic load | 2603.5 | 2602.3 | 2602.9 | 2600 |
Centrifugal load | 2628.7 | 2635.3 | 2642.7 | 2651.3 | ||
Centrifugal and Aerodynamic load | 2624.6 | 2630 | 2638.4 | 2644.5 | ||
3 | Second-order bending | Aerodynamic load | 3324.8 | 3325.5 | 3327.3 | 3327.1 |
Centrifugal load | 3447.6 | 3484.6 | 3525.8 | 3571.5 | ||
Centrifugal and Aerodynamic load | 3447.7 | 3484.7 | 3527.2 | 3572.1 | ||
4 | Second-order torsion | Aerodynamic load | 4969.7 | 4968.6 | 4970.5 | 4966.2 |
Centrifugal load | 5000.5 | 5008.6 | 5017.6 | 5028.4 | ||
Centrifugal and Aerodynamic load | 4995.2 | 5001.8 | 5012.7 | 5019.4 | ||
5 | Third-order bending | Aerodynamic load | 6195.6 | 6194.2 | 6194.3 | 6191.7 |
Centrifugal load | 6236.6 | 6248.6 | 6262.2 | 6277.6 | ||
Centrifugal and Aerodynamic load | 6235.7 | 6246.8 | 6261.2 | 6275.1 | ||
6 | Third-order torsion | Aerodynamic load | 6893.8 | 6894.0 | 6897.2 | 6894.6 |
Centrifugal load | 6999.0 | 7031.3 | 7068.0 | 7109.8 | ||
Centrifugal and Aerodynamic load | 6996.4 | 7028.0 | 7067.4 | 7105.9 |
Disclaimer/Publisher’s Note: The statements, opinions and data contained in all publications are solely those of the individual author(s) and contributor(s) and not of MDPI and/or the editor(s). MDPI and/or the editor(s) disclaim responsibility for any injury to people or property resulting from any ideas, methods, instructions or products referred to in the content. |
© 2024 by the authors. Licensee MDPI, Basel, Switzerland. This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution (CC BY) license (https://creativecommons.org/licenses/by/4.0/).
Share and Cite
Lin, H.; Bao, H.; Zhang, H.; Zhao, F.; Wang, J. Strength and Vibration Analysis of Axial Flow Compressor Blades Based on the CFD-CSD Coupling Method. Appl. Sci. 2024, 14, 7432. https://doi.org/10.3390/app14167432
Lin H, Bao H, Zhang H, Zhao F, Wang J. Strength and Vibration Analysis of Axial Flow Compressor Blades Based on the CFD-CSD Coupling Method. Applied Sciences. 2024; 14(16):7432. https://doi.org/10.3390/app14167432
Chicago/Turabian StyleLin, Haiwei, Hong Bao, Huaihuai Zhang, Feifei Zhao, and Junli Wang. 2024. "Strength and Vibration Analysis of Axial Flow Compressor Blades Based on the CFD-CSD Coupling Method" Applied Sciences 14, no. 16: 7432. https://doi.org/10.3390/app14167432