The role of radial secondary flow in the process of rotating stall for a 1.5-stage axial compressor

Li, Hefei; Zheng, Qun; Chen, Zhenyi; Duan, Yu; Jiang, Bin; Benini, Ernesto

doi:10.1016/j.ast.2021.106752

Cited by 15 publications

(3 citation statements)

References 16 publications

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“…More specifically, the choice of tip clearance may alter both the radial distribution of blade loading and contribute to influencing the breakdown of the flow in the tip region [29][30][31]. Hence, for the present study, the use of tip-clearance would introduce substantial additional difficulties for interpreting the flow, since tip clearance leakage vortices play a decisive role in the origin of rotating instabilities and stall inception [32]. Furthermore, the optimization of the VINK compressor [33], was performed for zero tip clearance and hence including a tip clearance would effectively mean studying a non-optimal compressor.…”

Section: Approachmentioning

confidence: 97%

Analysis of Blade Aspect Ratio Influence on High-Speed Axial Compressor Performance

Silva,

Grönstedt,

Xisto

et al. 2024

Preprint

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The ratio between blade height and chord, named aspect ratio (AR), plays an important role in compressor aerodynamic design. Once selected, it influences stage performance, blade losses, and the stage stability margin. The choice of the design AR involves both aerodynamic and mechanical considerations, and a reasonable aim is frequently to achieve a desired operating range while maximizing efficiency. For a fixed set of aerodynamic and geometric parameters there will be an optimal choice in AR that achieves a maximum efficiency. However, for a state-of-the-art aero-engine design optimality means multi-objective optimality, that is reaching the highest possible efficiency for a number of operating points while achieving a sufficient stability margin. To this end, the influence of the AR on the performance of the first rotor row of a multistage multi-objective high-speed compressor design is analyzed. A careful setup of the high-speed aerodynamic design problem allows the effect of the AR to be isolated. Close to the optimal AR, only a modest efficiency variation is observed, but a considerable change in compressor stability margin (SM) is noted. Decreasing the AR allows for an increasing efficiency, but at the expense of a reduced surge margin. This allows the designer to trade efficiency for stability. Increasing the AR, however, is shown to reduce both surge margin and efficiency, hence a distinct optimality in stability is observed for the analyzed rotor blade row. In this work, the optimality in surge margin with respect to AR is observed whereas a close to optimal efficiency. The predicted range from AR=1.10 to AR=1.64, is only indicative, considering that the definition of a multi-objective optimality requires balancing efficiency and surge margin and that the choice of balancing these two criteria requires making a design choice along a pareto optimal front.

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Section: Approachmentioning

confidence: 97%

Analysis of Blade Aspect Ratio Influence on High-Speed Axial Compressor Performance

Silva,

Grönstedt,

Xisto

et al. 2024

Preprint

View full text Add to dashboard Cite

show abstract

“…More specifically, the choice of tip clearance may both alter the radial distribution of blade loading and contribute to influencing the breakdown of the flow in the tip region [28][29][30]. Hence, for the present study, the use of tip clearance would have introduced substantial additional difficulties for interpreting the flow, since tip clearance leakage vortices play a decisive role in the origin of rotating instabilities and stall inception [31]. Furthermore, the optimization of the VINK compressor [32] was performed for zero tip clearance, and hence including tip clearance would effectively have meant studying a non-optimal compressor.…”

Section: Approachmentioning

confidence: 97%

Analysis of Blade Aspect Ratio’s Influence on High-Speed Axial Compressor Performance

Silva,

Grönstedt,

Xisto

et al. 2024

Aerospace

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The ratio between blade height and chord, named the aspect ratio (AR), plays an important role in compressor aerodynamic design. Once selected, it influences stage performance, blade losses and the stage stability margin. The choice of the design AR involves both aerodynamic and mechanical considerations, and an aim is frequently to achieve the desired operating range while maximizing efficiency. For a fixed set of aerodynamic and geometric parameters, there will be an optimal choice of AR that achieves a maximum efficiency. However, for a state-of-the-art aero-engine design, optimality means multi-objective optimality, that is, reaching the highest possible efficiency for a number of operating points while achieving a sufficient stability margin. To this end, the influence of the AR on the performance of the first rotor row of a multistage, multi-objective, high-speed compressor design is analyzed. A careful setup of the high-speed aerodynamic design problem allows the effect of the AR to be isolated. Close to the optimal AR, only a modest efficiency variation is observed, but a considerable change in compressor stability margin (SM) is noted. Decreasing the AR allows for increasing efficiency, but at the expense of a reduced surge margin. This allows the designer to trade efficiency for stability. Increasing the AR, however, is shown to reduce both the surge margin and efficiency; hence, a distinct optimality in stability is observed for the analyzed rotor blade row. In this work, optimality in the surge margin with respect to the AR is observed, whereas there is a close to optimal efficiency. The predicted range from AR = 1.10 to AR = 1.64 is only indicative, considering that the definition of multi-objective optimality requires balancing efficiency and the surge margin and that the choice of balancing these two criteria requires making a design choice along a pareto optimal front.

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“…The research on the leakage vortex structure of tip clearance and its correlation with rotating stall has received extensive attention [1][2]. However, the effect of tip clearance on blade aeroelasticity is rarely studied.…”

Section: Introductionmentioning

confidence: 99%

Influence of tip leakage flow on the aerodynamic damping of compressor blade torsional vibration

Zhang¹,

X²,

Ren³

2022

Vib. proced.

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Based on harmonic balance calculation technology with a single-passage phase-lag periodic boundary, the influence of tip gap size on the aerodynamic damping characteristics of rotor for first-order torsional vibration is analyzed with energy method. This research shows that the aerodynamic damping coefficient of the blade has a parabolic distribution law of first decreasing and then increasing with the increase of the tip clearance size. There is a most dangerous clearance value of torsional flutter characteristics in the blade, and the aerodynamic damping under this clearance is 12.67 % lower than the maximum damping value. The influence of the leakage flow on the time-averaged flow field near the blade tip leads to significant differences in the local aerodynamic work. In addition, the effect of leakage flow on the amplitude and phase of the local first-order unsteady pressure also bring about a significant influence on local aerodynamic work near blade tip.

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The role of radial secondary flow in the process of rotating stall for a 1.5-stage axial compressor

Cited by 15 publications

References 16 publications

Analysis of Blade Aspect Ratio Influence on High-Speed Axial Compressor Performance

Analysis of Blade Aspect Ratio Influence on High-Speed Axial Compressor Performance

Analysis of Blade Aspect Ratio’s Influence on High-Speed Axial Compressor Performance

Influence of tip leakage flow on the aerodynamic damping of compressor blade torsional vibration

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