Abstract
The transonic axial flow compressor Rotor 37 is subjected to the combined action of thermal load, centrifugal load, and aerodynamic load in real work. The difference in load will cause the blade deformation and the size and distribution of stress to change. And it will cause the vibration frequency of the blade to change compared with the static state at room temperature. This paper studies the compressor blades based on the fluid-thermal-structure coupling method, and comprehensively considers the combined effects of thermal load, centrifugal load and aerodynamic load on the compressor blades. The results of the study show: that when the thermal load acts on the blade alone, it will have less impact on the blade deformation and greater impact on the stress, but when coupled with other loads, it will have a greater impact on the blade deformation and stress. In the case of fluid-thermal-structure coupling, the deformation of the compressor blade will first increase and then decrease with the increase of mass flow, and the change of stress will not decrease with the increase of mass flow. Rotation speed will affect the change trend of blade stress with mass flow. Compared with the static state at room temperature, the natural frequency of the blade under fluid-thermal-structure coupling has undergone a huge change. The first-order vibration frequency has increased by 25.77 %. It can be seen from the Campbell diagram that the compressor blade has a resonance at about 63 % and 98 % Point, in this case, the blade is prone to resonance, and more attention should be paid.
Highlights
Compressor blade is one of the key parts of the engine, its safety and stability directly determine the performance of the engine
The modal analysis of the blade under actual working conditions is to use the comprehensive stress generated by the aerodynamic load, thermal load and centrifugal load on the blade in actual work as the prestress to perform the modal analysis on the blade
Based on the CFD/CSD fluid-thermal-structure coupling method, this paper analyzes the influence of the aerodynamic load, thermal load and centrifugal load of the transonic axial flow compressor on the structural characteristics of the blade
Summary
Compressor blade is one of the key parts of the engine, its safety and stability directly determine the performance of the engine. The two-way fluid-thermal-structure coupling three-field coupling method is used to simulate the compressor blades to analyze the stress and deformation of the blades under comprehensive loads, and use this as the prestress to perform modal analysis on the blades, and calculate the load And the natural frequency of the blade under no load, and draw the Campbell diagram of the blade to judge whether the blade will resonate It provides reliable data for preventing blade stress damage, blade resonance, and prolonging the service life of compressor blades, and provides theoretical basis for blade structure optimization design
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