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CRACK FAILURE ANALYSIS OF LOW PRESSURE TURBINE SHAFT OIL PASSAGE HOLE OF AERO-ENGINE
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.
CRACK FAILURE ANALYSIS OF LOW PRESSURE TURBINE SHAFT OIL PASSAGE HOLE OF AERO-ENGINE
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.
CRACK FAILURE ANALYSIS OF LOW PRESSURE TURBINE SHAFT OIL PASSAGE HOLE OF AERO-ENGINE
WANG Xuemin (author) / LU Xuping (author) / SHEN Lian (author) / GU Yuanxing (author) / WU Chen (author) / GUO Jianying (author) / XU Jingpei (author)
2025
Article (Journal)
Electronic Resource
Unknown
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