## 1 Introduction  
With the advancement of aviation engine technology, axial flow compressors, as crucial components of aviation engines, face increasingly stringent demands on overall performance. Consequently, in recent years, there has been an unparalleled development in turbomachinery, with design trends gradually shifting towards higher pressure ratios, improved efficiency, and broader operating ranges. However, the working environment for axial flow compressor blades is highly hostile, subjecting them to prolonged exposure to high temperatures, velocities, and pressures. During operation, compressor blades encounter various factors such as centrifugal loads, aerodynamic loads, thermal loads, and vibrations [1]. If blade vibration or fracture occurs, it will result in significant economic losses for the entire unit. Studies indicate that over 65% of compressor failures are blade-related [2]. According to data from a complete operational cycle of aviation engines and external maintenance test runs, compressor rotational speeds vary based on the aircraft's flight status. Under different rotational speed conditions, the centrifugal and aerodynamic loads experienced by the blades exhibit notable variations. Therefore, conducting strength verification of compressor blades, assessing the influence of loads on blade stress and strain, and identifying potential resonance points during operation are of paramount practical and guiding significance. Such measures can prevent blade-resonance-induced damage, thereby enhancing equipment economy and safety. In recent years, scholars both domestically and internationally have conducted extensive research on the structural performance of compressors. [PERSON] et al. [3] utilized finite element analysis to simulate the stress on a simplified impeller model, revealing that an increase in impeller rotational speed results in elevated stress levels, with centrifugal loads exhibiting a more pronounced effect. The interface between the blades and the hub emerges as the location of maximum stress. [PERSON] et al. [4] conducted a finite element analysis study on compressor blades. The research findings indicate that despite the large number of stages in the compressor, the methods utilized in the study are applicable across the entire compressor range, and vibration stress curves were plotted. Additionally, vulnerable areas of the impeller were detailed, guiding for assessing the lifespan of impeller blades. In recent years, research on the structural performance and vibration of axial flow compressor blades based on the CFD-CSD coupling method has primarily focused on coupling strategies and the numerical solution accuracy of aerodynamic forces, stresses, and strains [5; 6]. [PERSON] et al. [7] conducted numerical simulation studies on the aeroelasticity of compressor blades using fluid-structure coupling methods. They analyzed the dynamic stress and strain of the blades caused by aerodynamic impacts and assessed whether compressor blade flutter would occur. [PERSON] [8] conducted simulation studies on the structure of turbochargers' compressors, analyzing the deformation and stress distribution of blades under fluid dynamics, thereby offering theoretical foundations for structural optimization. [PERSON] et al. [9] and others studied the compressor impeller of a certain type of micro-turbine engine, analyzing the formation mechanism of thermal loads and their impact on impeller stress and strain. [PERSON] [10] utilized the DS module of the ANSYS Workbench platform and the APDL language as the interface for transferring surface load data of blades, conducting a numerical simulation study on the internal flow of a transonic fan in a certain type of turbofan engine with fluid-structure coupling. The research findings demonstrated that the fluid-structure coupling-based numerical simulation was closer to experimental results, validating the effectiveness of this method. [PERSON] et al.