Abstract
In this study, 3D models of a compressor blade for an aero engine with three different levels of surface accuracy (with 4, 6 and 10 section profiles) were obtained via reverse engineering by fitting point-cloud data. Then, finite element and flow-field models of the blade were established and validated. The vibration characteristics of the blade under typical operating conditions were analyzed by considering the interaction between the aerodynamic load by airflow and the centrifugal load by blade rotating. The results showed that, under complex centrifugal and aerodynamic loads, the three blade models differed significantly in their high-order dynamic frequencies, and the modal frequencies that were dominated by a torsional mode of vibration were sensitive to the aerodynamic load. Hence, considering both the aerodynamic excitation and the centrifugal load increased the accuracy of the numerical computation of the blade vibration characteristics. Moreover, a comparison of the computational results from the three blade models showed that models B6 and B10 differed only insignificantly, and B6 decreased the complexity of the modeling process while satisfying the required computational accuracy. Thus, model B6 is the best option for engineering analysis and computation.
Highlights
In the thermodynamic cycle of an aero engine, an axial flow compressor compresses air and supplies a continuous flow of pressurized air to the combustion chamber
The aerodynamic load induced by the interaction between the airflow and blade rotation is the major causal factor of the blade vibration
In model B4, the maximum aerodynamic pressure zone was mainly located near the blade tip, whereas in model B6, the maximum aerodynamic pressure zone was mainly located at 3/4 blade height
Summary
In the thermodynamic cycle of an aero engine, an axial flow compressor compresses air and supplies a continuous flow of pressurized air to the combustion chamber. The blade is a major functional component of the compressor, which operates in an environment of continuous high rotation speed, high pressure, and vibration [1]. As the engine’s rotational speed and pressure ratio increase, the operating environment of the blade will become more adverse, and its vibration and fatigue behaviors will become more complex, resulting in a greater requirement for analysis of the vibration characteristics and structural fatigue design of high-speed rotating blades. The accuracy of blade modeling can be greatly improved by increasing the number of curves used to fit the blade profile. This enables a blade model that better approximates the surface characteristics of the real blade to be obtained from reverse engineering [4]
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