受高温、高压和离心力共同作用，航空发动机叶型在工作状态（热态）下会与加工状态（冷态）产生差异。为了消除这一差异对叶片气动性能的影响，本文搭建了叶片热态-冷态仿真转换流程：利用APDL实现有限元计算后叶片数据的自动传递，并通过自编程序解决了叶型离散数据点混乱和光顺性不足的问题，构建了拟合求取二维叶型参数和叶型重合度评估检验的方法。以某轴流压气机叶片为研究对象，进行叶片在离心、气动、温度载荷作用下的预变形设计，将气动设计叶型经热态-冷态变形转化为加工叶型，并对方法准确性进行评估。结果表明该转换方法精确度高，叶型效率偏差小于0.1%。本文研究补充了有限元计算后叶型参数获取、拟合、重新参数化设计的空缺，能够提升考虑冷热态下叶片设计的效率，具备工程应用意义。

Under the combined effects of high temperature, high pressure, and centrifugal force, the blade profile of an aero-engine undergoes variations between the operational (hot) state and the manufacturing (cold) state. To reduce the impact of these variations on aerodynamic performance, this paper establishes a simulation-based conversion process between the hot and cold states of the blades. Finite element analysis (FEA) was automated using APDL to facilitate the transfer of blade data. A custom-developed program was also developed to address issues of scattered discrete data points and insufficient smoothness in the blade profile. A method was developed to fit and evaluate 2D blade profile parameters and ensure profile conformity. A specific axial-flow compressor blade was selected for the study, where pre-deformation design was applied considering centrifugal, aerodynamic, and thermal loads. The aerodynamic blade profile was converted from the hot state to the cold state, resulting in a manufacturing profile, and the accuracy of this method was evaluated. The results demonstrate that the proposed conversion method is highly accurate, with a blade profile efficiency deviation of less than 0.1%. This study addresses the gap in parameter acquisition, fitting, and re-parameterization of blade profiles post-FEA, enhancing blade design efficiency for both hot and cold states, with significant engineering application value.

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黑龙江省优秀青年基金(YQ2021E023)