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Crack failure analysis of low pressure turbine shaft oil passage hole of aero-engine
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Xuemin WANG1, 2, Xuping LU1, Lian SHEN1, Yuanxing GU1, Chen WU1, Jianying GUO1, Jingpei XU1
Journal of Mechanical Strength | 2025, 47(2) : 37 - 43
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Journal of Mechanical Strength | 2025, 47(2): 37-43
• Fatigue∙Damage∙Fracture∙Failure Analysis •
Crack failure analysis of low pressure turbine shaft oil passage hole of aero-engine
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Xuemin WANG1, 2, Xuping LU1, Lian SHEN1, Yuanxing GU1, Chen WU1, Jianying GUO1, Jingpei XU1
Affiliations
  • 1.AECC Sichuan Gas Turbine Research Establishment, Chengdu 610500, China
  • 2.School of Mechanical and Electrical Engineering, University of Electronic Science and Technology of China, Chengdu 611731, China
Published: 2025-02-15 doi: 10.16579/j.issn.1001.9669.2025.02.005
Outline
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In order to investigate the nature and causes of the cracked passage hole of the low-pressure turbine shaft of aero-engine during the high and low circumference compound fatigue test, the low-pressure turbine shaft crack location was examined in appearance, fracture analysis, surface inspection, metallographic organization, finite element analysis and crack expansion simulation.The results show that the low-pressure turbine shaft passage hole crack failure is a fatigue crack, which is caused by the incomplete removal of the remelting layer after the passage hole is cut by electrical discharge machining,resulting in the existence of part of the unremoved remelting layer and visible microcracks on the internal surface, and the fatigue crack sprouted and crack expansion occurred under the action of large high and low circumferential composite load,thus leading to the passage hole crack failure. The initial crack length is estimated to be between 0.2-0.3 mm by the crack expansion simulation analysis. In order to ensure the processing quality of the through oil hole, considering the poor processing accessibility of this location, it is suggested that special tooling can be designed and the machining technology can be used for processing, on the basis of ensuring the processing, fundamental eliminate the influence of the remelting layer.

Low pressure turbine shaft  /  Failure analysis  /  Remelting layer  /  Fatigue fracture  /  Finite element analysis  /  Crack expansion simulation  /  Aero-engine
Xuemin WANG, Xuping LU, Lian SHEN, Yuanxing GU, Chen WU, Jianying GUO, Jingpei XU. Crack failure analysis of low pressure turbine shaft oil passage hole of aero-engine[J]. Journal of Mechanical Strength, 2025 , 47 (2) : 37 -43 . DOI: 10.16579/j.issn.1001.9669.2025.02.005
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  • Basic Research Programs in Aerospace Dynamics
Appendix
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Year 2025 volume 47 Issue 2
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60
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Article Info
doi: 10.16579/j.issn.1001.9669.2025.02.005
  • Receive Date：2023-05-06
  • Online Date：2026-03-18
  • Published：2025-02-15
Article Data
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History
  • Received：2023-05-06
  • Revised：2023-09-08
Funding
Basic Research Programs in Aerospace Dynamics
Affiliations
    1.AECC Sichuan Gas Turbine Research Establishment, Chengdu 610500, China
    2.School of Mechanical and Electrical Engineering, University of Electronic Science and Technology of China, Chengdu 611731, China

Corresponding:

WANG Xuemin, E-mail：
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表12种不同金属材料的力学参数
科
Family		 属数
Number of
genus		 种数
Number of
species		 占总种数比例
Percentage of
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鹅膏菌科Amanitaceae 2 11 5.26 鹅膏菌属 Amanita 10 4.78
小菇科 Mycenaceae 2 12 5.74 丝盖伞属 Inocybe 5 2.39
多孔菌科 Polyporaceae 8 14 6.70 蜡蘑属 Laccaria 5 2.39
红菇科 Russulaceae 3 23 11.00 小皮伞属 Marasmius 6 2.87
小菇属 Mycena 11 5.26
光柄菇属 Pluteus 5 2.39
红菇属 Russula 17 8.13
栓菌属 Trametes 5 2.39
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