Influence of circumferential grooves on the aerodynamic and aeroelastic stabilities of a transonic fan

Cong, Jiqing; Jing, Jianping; Dai, Zezeng; Cheng, Jianhua; Chen, Changmin

doi:10.1016/j.ast.2021.106945

Cited by 11 publications

(2 citation statements)

References 15 publications

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“…And all the frequency deviations in Figure . 4 are less than 2%. Therefore, the 1B mode data of the blade with design tip clearance, which also reaches an agreement with the research of Cong et al [15], is applied in flutter simulations for different tip clearances. Besides, due to the different grid distributions of the solid domain and fluid domain, radial basis function (RBF) interpolation method is used to extend 1B mode data to fluid domain grids.…”

Section: Finite Element Modelsupporting

confidence: 82%

“…As a representative modern transonic axial compressor rotor, NASA Rotor 67 is adopted in this paper to study the flutter stability for various tip clearance models at different NDs. Due to the detailed aerodynamic characteristics and geometry data in the experiment conducted by Strazisar et al [14], Rotor 67 has been widely used in flutter researches [15][16][17], which can provide a certain reference to the flutter analysis in this paper. The meridian plane with aerodynamic survey locations is illustrated in Figure 1.…”

Section: Test Casementioning

confidence: 99%

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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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Section: Finite Element Modelsupporting

confidence: 82%