Simulation and Experimental Study of Gas Turbine Blade Tenon-Root Detachment on Spin Test
Abstract
:1. Introduction
2. Numerical Simulation
2.1. Containment-Coefficient Methods
2.2. Containment Simulation Analysis
2.2.1. The Single-Blade Containment Numerical Simulation
2.2.2. The Dual-Blade Containment Numerical Simulation
3. Test Verification
3.1. Containment Test Set-Up
3.2. Experimental Results
3.2.1. The Single-Blade Containment Test Results
3.2.2. The Dual-Blade Containment Test Results
4. Discussion
4.1. Simulation and Experimentation Comparison
4.2. Influence of Blade Shape in Casing Containment
4.3. Influence of Dual-Blade Collision in Casing Containment
4.4. GasTurbine Single-Blade Containment Curve
Critical Speed (r/min) | 41,500 | 43,500 | 45,500 | 47,500 | 49,500 | 51,500 | 53,500 | |
Casing Thinkness (mm) | Single blade | 2.17 | 2.28 | 2.38 | 2.50 | 2.60 | 2.69 | 2.78 |
Dual blade | 2.23 | 2.32 | 2.41 | 2.55 | 2.64 | 2.72 | 2.82 |
Critical Speed (r/min) | 41,500 | 43,500 | 45,500 | 47,500 | 49,500 | 51,500 | 53,500 | |
Casing Thinkness (mm) | Single blade | 1.81 | 1.89 | 1.99 | 2.05 | 2.11 | 2.19 | 2.26 |
Dual blade | 1.85 | 1.92 | 2.02 | 2.10 | 2.21 | 2.31 | 2.42 |
5. Conclusions
- (1)
- The impact response process of a single gas turbine blade detachment mainly consists of three stages: the tip of the blade hitting the casing, the root of the blade hitting the casing, and the blade sliding along the inner wall of the casing. The maximum damage to the casing is mainly caused by the impact of the blade root in the second stage.
- (2)
- Due to the longer blade structure of the gas turbine blade B compared to the blade A, the energy of the blade root impacting the casing is relatively lower. Therefore, the safety factor of the gas turbine blade B is higher than that of the blade A.
- (3)
- It was observed that dual-blade containment tests resulted in more severe damage compared to single-blade tests. The simulations showed that in dual-blade tests, the impact energy was higher due to the influence of the first blade, leading to larger damage. This finding highlights the critical role of interaction effects between successive blades in determining containment outcomes, shedding light on nuanced failure mechanisms critical for engine safety assessments.
- (4)
- Based on the numerical simulation results, curves of the containment speed for gas turbine blade detachment under different casing thicknesses are proposed. The fitting degrees of the containment curves for the blade A and B are 0.994 and 0.997, respectively. This contributes to further optimizing shell design, improving the safety and reliability of aircraft engines, and providing new ideas and methods for the development of the aviation engineering field.
Author Contributions
Funding
Data Availability Statement
Conflicts of Interest
References
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Material | J-C Constitutive Model Parameters | ||||
A/MPa | B/MPa | n | C | M | |
GH4169 | 872 | 1084 | 0.545 | 0.0134 | 1.3 |
K417 | 850 | 1090 | 0.65 | 0.014 | 1.1 |
Material | J-C Failure Model Parameters | ||||
D1 | D2 | D3 | D4 | D5 | |
GH4169 | 0.11 | 0.24 | 1.92 | 2.12 × 10−5 | 0.65 |
K417 | −0.1 | 0.24 | 0.45 | 0.011 | 3.84 |
Simulation ID | Simulation Model | Thickness (mm) | Spin Speed (r/min) | Results |
---|---|---|---|---|
A-1 | Single-blade model | 2.37 | 47,500 | Non-containment |
B-1 | 2.12 | 50,000 | Critical containment | |
A-2 | 2.37 | 45,125 | Critical containment | |
B-2 | 2.12 | 47,500 | Containment | |
A-3 | Dual-blade model | 2.37 | 47,500 | Non-containment |
B-3 | 2.12 | 50,000 | Non-containment | |
A-4 | 2.37 | 45,125 | Non-containment | |
B-4 | 2.12 | 47,500 | Containment |
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Yu, M.; Wang, J.; Xuan, H.; Xiong, W.; He, Z.; Qu, M. Simulation and Experimental Study of Gas Turbine Blade Tenon-Root Detachment on Spin Test. Aerospace 2024, 11, 629. https://doi.org/10.3390/aerospace11080629
Yu M, Wang J, Xuan H, Xiong W, He Z, Qu M. Simulation and Experimental Study of Gas Turbine Blade Tenon-Root Detachment on Spin Test. Aerospace. 2024; 11(8):629. https://doi.org/10.3390/aerospace11080629
Chicago/Turabian StyleYu, Maoyu, Jianfang Wang, Haijun Xuan, Wangjiao Xiong, Zekan He, and Mingmin Qu. 2024. "Simulation and Experimental Study of Gas Turbine Blade Tenon-Root Detachment on Spin Test" Aerospace 11, no. 8: 629. https://doi.org/10.3390/aerospace11080629