Aeroelastic vibration analysis of a 1.5 stage compressor

Zheng, Yao; Gao, Qingzhe; Yang, Hui; Xu, Kang

doi:10.1016/j.jppr.2019.11.001

Cited by 8 publications

(5 citation statements)

References 13 publications

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“…HGAE integrates a three-dimensional (3D) unstructured finitevolume compressible flow solver and a structured dynamic solver into one computing platform, which can solve the fluid-structure interaction in a coupled or uncoupled way. The CFD code has been developed and used for more than 18 years, and has been validated for various aerodynamic and aeroelastic cases [20][21][22][23][24].…”

Section: Methodsmentioning

confidence: 99%

“…For the rotor blades subjected to 19EO excitation arising from the IGV wake and IGV-R1 interactions (mode m 4 ), no matter which is dominant, the response will occur in BM6/4ND. This is because the aerodynamic wave number of the former is 19, which is higher than the half number of rotor blades (23), thus the 4ND response is excited through the spatial aliasing, while the mode m 4 will excite the 4ND response directly. Hence, the amplitude of the BM6/4ND modal force was computed, and the maximum vibration amplitude in Table 6 was calculated using Equation (8).…”

Section: Contribution Of Upstream Disturbances To Blade Vibration Amp...mentioning

confidence: 99%

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Forced Response Analysis of an Embedded Compressor Rotor Induced by Stator Disturbances and Rotor–Stator Interactions

2023

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Accurate predictions of the blade response in a multi-row compressor is one of the most important tasks within the design process of compressor blades. Some recent studies have shown that the decoupled method considering only the stator disturbances cannot obtain accurate results for cases with strong rotor–stator interactions, especially for the interaction between the rotor and downstream stator, and the coupled method with multi-row configurations is necessary. Factors determine what computational domains to model need to be clarified to find a balance between accuracy requirements and computational costs. To this end, this study conducted full-annulus unsteady calculations with decoupled and coupled configurations to investigate the forced response of an embedded compressor rotor induced by upstream and downstream stator disturbances and rotor–stator interactions, respectively. The results show that the upstream IGV disturbances were dominated by the wake, and the IGV and S1 potential fields had little effect on the R1 response. Meanwhile, the IGV–R1 interactions and S1–R1 interactions were dominated by one cut-on mode, respectively. The comparisons of the blade vibration amplitude and the unsteady pressure field calculated by decoupled and coupled methods revealed the mechanism of the forced response, namely, for the R1 response induced by upstream aerodynamic disturbances, the dominant excitation source was the IGV wake, and the blade vibration amplitude can be predicted by the decoupled method. In terms of the response induced by downstream disturbances, the cut-on S1-R1-interaction mode was dominant and the use of the decoupled method without considering its influence will lead to an inaccurate prediction. This study concluded that the formation process of rotor–stator interactions was the key factor that determines whether the decoupled method or coupled method should be used, and analogized a process independent of the downstream stator disturbance. The results can provide a preliminary configuration for accurate and efficient blade response predictions and explain the reason why including downstream stator vanes is very important.

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Section: Methodsmentioning

confidence: 99%

Section: Contribution Of Upstream Disturbances To Blade Vibration Amp...mentioning

confidence: 99%

Forced Response Analysis of an Embedded Compressor Rotor Induced by Stator Disturbances and Rotor–Stator Interactions

2023

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“…More details about the validations for aerodynamic and aeroelastic cases can be found in the literatures (e.g. Zheng, 2004;Zheng and Yang, 2011;Zheng et al, 2020).…”

Section: Methodsmentioning

confidence: 99%

Investigation of Lock-in Phenomenon of a Fle Fan

Zheng¹,

Gao²,

Ye³

et al. 2022

Proceedings of Global Power &Amp; Propulsion Society

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This study numerically investigates the lock-in phenomenon of a fan blade with a flat-tip leading edge. A fully coupled, fluid-structure interaction method was applied to obtain the unsteady flows coupled with the blade vibrations. The results show that the disturbances of the unsteady aerodynamics become locked to the structural vibration, which indicates a lockin phenomenon. For a fixed modal velocity as the initial excitation, the frequencies of the structured mode were altered around the natural frequency to determine the lock-in boundary. In the lock-in region, the vibration amplitude grew exponentially, thus the blade vibration was unstable. The spectra of the displacement and the unsteady pressure associated with the structural response and the aerodynamic disturbance exhibit discrete peaks. The absolute difference of the coupled aerodynamic wave number (AWN) and the nodal diameter (ND) was equal to the blade number. In the unlocked region, the blade vibration exhibits the characteristics of the limit cycle oscillation. The pressure spectra present broadband peaks and the AWN was not matched to the concerned ND. However, the AWN and the ND changed in the cases with different vibration frequencies, and it indicates that there was still a coupling between the aerodynamic disturbance and the structural vibration. The lock-in phenomenon was consistent with the occurrence of NSV, evidenced by the fact that the frequency and phase of the aerodynamic disturbance can be locked to the structural vibration pattern. Hence, NSV could be induced by the lock-in phenomenon.

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“…The intensity of tip clearance flow and the formation of tip clearance vortices [3,4] are strongly affected by the tip clearance variation. Besides, because the most part of aerodynamic work is concentrated in the blade tip region [5], the tip clearance which has close ties with complex tip clearance flow also has significant effects on the flutter stability. Nevertheless, researches about the effects of the tip clearance on the flutter stability have not reached an agreement.…”

Section: Introductionmentioning

confidence: 99%

“…When the blades vibrate at different NDs or inter-blade phase angles (IBPA), this effect will be changed, further leading to variations in blade flutter stability [11,12]. In addition, some researches [5,9,13] also found that the effects of tip clearance variations on the flutter stability are distinct at different NDs or IBPAs.…”

Section: Introductionmentioning

confidence: 99%

Influence mechanism of tip clearance on flutter stability with different aerodynamic coupling effects for transonic compressor

Xin,

He,

et al. 2024

J. Phys.: Conf. Ser.

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Flutter is a highly destructive aeroelastic problem in modern compressors, which hinders the improvements of aero-engine performance and reliability. Because the aerodynamic work is mainly concentrated in the blade tip region, the tip clearance which is associated to the complex tip clearance flow has a considerable effect on the flutter stability. In this paper, in order to investigate the influence mechanism of the tip clearance on the flutter stability at different nodal diameters (ND), a series of compressor models were established with different tip clearances based on a transonic compressor rotor. The aerodynamic damping at each ND is obtained by influence coefficient method (ICM), while phase-shifted boundary method (PSB) is adopted to analyze the influence of the tip clearance on the flutter stability at different NDs. The results indicate the worst flutter stability for each tip clearance always appears at ND=1, where the aerodynamic damping exhibits a nonmonotonic trend of increasing first and decreasing thereafter along with the rising tip clearance. Two kinds of action are exerted by the tip clearance flow on the flow structures to alter the flutter stability: one is the tip clearance vortices which is generated on the suction side and impinge on the pressure side; the other is the interference of tip clearance vortices to the shock wave and to the flow separation. Besides, the influence of the changing aerodynamic coupling effect makes the above action bring about more drastic fluctuations to the unsteady pressure. At larger NDs, the unsteady pressure amplitude and phase fluctuate more sharply for larger tip clearances. Therefore, diverse change trends of the aerodynamic damping with the increasing tip clearance appear at different NDs, while the impingement of tip clearance vortices on the adjacent pressure side has a constantly stabilizing effect at different NDs.

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Aeroelastic vibration analysis of a 1.5 stage compressor

Cited by 8 publications

References 13 publications

Forced Response Analysis of an Embedded Compressor Rotor Induced by Stator Disturbances and Rotor–Stator Interactions

Forced Response Analysis of an Embedded Compressor Rotor Induced by Stator Disturbances and Rotor–Stator Interactions

Investigation of Lock-in Phenomenon of a Fle Fan

Influence mechanism of tip clearance on flutter stability with different aerodynamic coupling effects for transonic compressor

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