Analyzing the aerodynamic damping of impellers with splitter blades using the fluid solid weak coupling method and its conclusions

Tech 2023-10-23 07:01:43 Source: Network

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With the continuous development of aircraft engine technology, the compressor of aviation engines is moving towards high-performance, small volume, and lightweight. However, during this process, the flutter problem of the fan blades gradually emerged. In order to improve the aeroelastic stability margin of turbomachinery, scholars have proposed many flutter suppression methods, including increasing damping, changing blade vibration characteristics, and adopting non harmonic design. With the continuous development of computational fluid dynamics and computer hardware, aerodynamic damping has gradually attracted widespread attention.

The progress in computational fluid dynamics and the improvement of experimental data have led to a shift in the study of aerodynamic damping from experimental to numerical calculations. However, most studies are limited to analyzing the impeller structure of a single blade or the same blade, and there is relatively little research on aerodynamic damping for impellers with large and small blade structures.

The research object of this article is the centrifugal impeller of a small aircraft turboshaft engine, which mainly provides auxiliary power for the aircraft. The goal of this study is to conduct aerodynamic damping simulation on centrifugal impellers with large and small blade structures. By analyzing the vibration state of the impeller, a corresponding aerodynamic damping calculation model is established, and the influence of the circumferential position of the splitter blades on the aerodynamic damping of the impeller is explored. The purpose of the study is to provide strong references for the design and simulation of impeller structures with large and small blades.

In order to achieve this goal, modal analysis of the blades was first conducted to determine their natural frequencies and corresponding vibration modes. Then, harmonic response analysis was conducted to obtain the vibration response of the centrifugal impeller under unsteady aerodynamic forces. Finally, a fluid structure coupling analysis was conducted using finite element software. Through dynamic grid technology, the points on the impeller blades were subjected to harmonic vibration according to specific vibration modes to obtain the unsteady aerodynamic damping of the blades within a specific frequency range.

The research results indicate that aerodynamic damping plays an important role in the vibration of centrifugal impellers. The circumferential position of the splitter blades has a significant impact on aerodynamic damping, and different positions of the splitter blades can lead to different aerodynamic damping of the impeller. In addition, this article also explored the relationship between aerodynamic damping and blade surface flow field, and found that the magnitude of aerodynamic damping mainly depends on the work done by the aerodynamic force on the blade within a cycle. Therefore, changes in circumferential position will affect the amplitude and phase of unsteady pressure on the blade surface, thereby affecting aerodynamic damping.

This study provides a new approach for the design of impellers with large and small blade structures, where the circumferential position of the splitter blades can be adjusted appropriately according to demand to improve the aerodynamic and elastic stability of the impeller. This has positive implications for the performance and stability of aircraft engines.

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