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| Hot Corrosion Analysis and Improvement of Gas Turbine Rotor Blades of Turboshaft Engines |
| Received:October 23, 2023 Revised:November 17, 2023 |
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| DOI：10.7643/issn.1672-9242.2023.12.004 |
| KeyWord:turboshaft engine turbine blade hot corrosion fatigue failure mechanism analysis improvement measures |
| Author | Institution |
| YE Fei |
Zhuzhou Regional Aviation Military Office, Hunan Zhuzhou , China |
| KUANG Qiao |
Zhuzhou Regional Aviation Military Office, Hunan Zhuzhou , China |
| LI Jun |
Zhuzhou Regional Aviation Military Office, Hunan Zhuzhou , China |
| TENG Guan-hong-wei |
Zhuzhou Regional Aviation Military Office, Hunan Zhuzhou , China |
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| Abstract: |
| In order to improve the structural integrity, safety, and reliability of the working blades of aviation engine gas turbines. This paper studied the hot corrosion-fatigue failure mechanisms of gas turbine rotor blades, including the structural failure mode, the distribution law of corrosion pits, as well as the erosion and oxidation mechanisms of thermal barrier coating and blade superalloy. The results showed that the surface coating corrosion spalling occurred in the high friction coefficient area of the gas turbine blade under the action of high temperature gas scour effect and hot salt corrosion. The corrosion pit was formed after the blade alloy substrate of the spalling part of the coating was oxidized and eroded by high temperature gas. The protrusions or depressions on the surface of corrosion pits caused stress concentration, which accelerated the initiation of fatigue cracks and finally lead to fatigue fracture of blades. The chemical nature of corrosion and oxidation of high temperature resistant coating and nickel-based alloy matrix on gas turbine rotor blades caused by typical corrosive substances is investigated. Finally, suggestions for improving the thermal corrosion of gas turbine rotor blades are put forward, which can provide useful reference for preventing the thermal corrosion of aviation turboshaft engines. |
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