Active flow control by means of endwall synthetic jet on a high-speed compressor stator cascade

Qin, Yong; Song, Yanping; Chen, Fu; Wang, Ruoyu; Liu, Huaping

doi:10.1177/0957650917748736

Cited by 13 publications

(7 citation statements)

References 26 publications

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“…The schematic and geometric parameters of the baseline cascade are shown in Figure 1 and Table .1. 26,27 The design inflow angle (β 1k ) is 42 [deg]. The aspect ratio of the baseline cascade blades is 1, emphasizing the secondary flow and corner separation effects.…”

Section: Geometric Parameters and Operating Conditions Of Baseline Co...mentioning

confidence: 99%

The effect of the blended blade and end wall three-dimensional profiling design on cascade

Dong

Chu

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Blended Blade and End Wall (BBEW), a passive control method, has been employed in the turbomachinery field and verified to improve compressor performance effectively. In this paper, a new profiling method, based on suction surface parameterization, is proposed to enhance the flexibility and three-dimensional characteristics of BBEW profiling. The new profiling method is applied to a high subsonic-speed and highly loaded compressor cascade. The aim is to investigate effective flow control rules and practical design guidelines under multi-operating conditions. First, the design method for the experiential formula is established, and the relationship between the profiling control mechanism and the profiling geometry feature is investigated in the entire three-dimensional design space. Then, comparing different radian pattern profilings on design and stall conditions, a series of quantitative analyses and flow field analyses are conducted to discuss flow control mechanism. The numerical results verify that the three-dimensional BBEW design brings a more positive effect on corner separation. The primary flow control rule is enhancing the driving force at the blade root, which can effectively increase the kinetic energy of the low-energy fluid in the corner region and reduce loss. However, design and stall conditions also have specific differences in the mechanism of loss reduction. It mainly focuses on the aggravation of mixing loss when the low-energy fluid obtains more kinetic energy on design condition, but the problem hardly exists in stall condition. Thus, a larger radian pattern is beneficial to controlling the flow on design condition, but the stall condition is the opposite.

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Section: Geometric Parameters and Operating Conditions Of Baseline Co...mentioning

confidence: 99%

The effect of the blended blade and end wall three-dimensional profiling design on cascade

Dong

Chu

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Zheng et al (2006) verified the effectiveness of arranging synthetic jets on the suction surface of the blade and the casing respectively for flow separation control on a compressor cascade test bench. Using a highspeed compressor cascade as numerical simulation object, Qin et al (2017) took a low speed and high speed compressor cascades as numerical simulation objects, carried out a parametric study on the synthetic jet of suction surface and endwall, and revealed the mechanism of the synthetic jet to control the corner separation of the cascade and reduce the loss.…”

Section: Introductionmentioning

confidence: 99%

Effect of Active Flow Control of Endwall Synthetic Jet on the Performance of a Transonic Axial Compressor

2021

JAFM

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In order to improve the performance of a high-load transonic axial compressor, this paper proposes a method of applying endwall synthetic jet to the casing for active flow control. Taking NASA Rotor35 as the research object, the aerodynamic performance of the compressor is numerically calculated by applying three sets of synthetic jets with different excitation parameters at five different axial positions of 0%Ca, 25%Ca, 50%Ca, 75%Ca and 96.15%Ca. The results show that the three parameters of excitation position, jet peak velocity and jet frequency all have an effect on the performance of the compressor. The excitation position has the greatest influence on the flow margin of the compressor, and the best position is 25%Ca. After the jet peak velocity is increased from 100m/s to 150m/s, the flow margin, total pressure ratio and efficiency of the compressor are not greatly improved, which shows that the impact of the jet peak velocity is not as good as the excitation position. After continuing to increase the excitation frequency of the synthetic jet from 600Hz to 1200Hz, although the flow margin of the compressor is slightly reduced, the total pressure ratio and efficiency are further improved. This shows that there may be a threshold for the jet frequency, and only when the jet frequency is greater than the threshold can the overall aerodynamic performance of the compressor be improved.

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“…Zheng et al 15,16 verified the effectiveness of arranging synthetic jet on the suction surface of the blade and the casing, respectively, on the control of flow separation on the compressor cascade test bench. Qin et al 17,18 carried out a parametric study on the suction surface and the endwall synthetic jet, and revealed the mechanism of the synthetic jet to control the angle separation of the cascade and reduce the loss. Benini et al 19,20 arranged synthetic jet on the suction surface of the transonic compressor NASA Rotor 37.…”

Section: Introductionmentioning

confidence: 99%

Parametric study on active flow control of a transonic axial compressor rotor using endwall synthetic jet

Guang

Chu

Zhang

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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High-load axial compressor is the mainstream of current compressor design and development. In order to improve the aerodynamic performance of high-load axial compressor, an active flow control method in which a synthetic jet is applied to the endwall is proposed. Taking the transonic axial compressor NASA Rotor 35 as the research object, using a single factor analysis method, the influence of five different excitation positions, three different excitation frequencies, and three different jet peak velocities on the aerodynamic performance of the compressor was studied in turn, and obtained the influence law of the endwall synthetic jet excitation parameters. The results show that all three parameters have important effects on the performance of the compressor. Among the excitation parameters studied in this paper, there is an optimal excitation position of 25% Ca. When excited at this position, the flow margin of the compressor is expanded the most. On the basis of maintaining the optimal excitation position and the maximum jet peak velocity, the calculation results found that the jet frequency has little effect on the compressor’s near stall flow rate, but has a great impact on the total pressure ratio and efficiency. The pressure ratio and efficiency increase with the increase of the excitation frequency. However, there seems to be a threshold of the excitation frequency. Only when the excitation frequency is greater than the threshold can the total pressure ratio and efficiency be higher than the prototype compressor. The jet peak velocity has the smallest impact on the compressor performance. Based on the optimal excitation position and the excitation frequency exceeding the threshold, even if the jet peak velocity is small, the compressor can obtain a higher flow margin, total pressure ratio, and efficiency than the prototype compressor. As the jet peak velocity increases, the performance of compressor can be further improved.

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Active flow control by means of endwall synthetic jet on a high-speed compressor stator cascade

Cited by 13 publications

References 26 publications

The effect of the blended blade and end wall three-dimensional profiling design on cascade

The effect of the blended blade and end wall three-dimensional profiling design on cascade

Effect of Active Flow Control of Endwall Synthetic Jet on the Performance of a Transonic Axial Compressor

Parametric study on active flow control of a transonic axial compressor rotor using endwall synthetic jet

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